CN107284646B - Cockpit entrance and exit door frame structure and design method thereof - Google Patents
Cockpit entrance and exit door frame structure and design method thereof Download PDFInfo
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- CN107284646B CN107284646B CN201710547222.9A CN201710547222A CN107284646B CN 107284646 B CN107284646 B CN 107284646B CN 201710547222 A CN201710547222 A CN 201710547222A CN 107284646 B CN107284646 B CN 107284646B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1407—Doors; surrounding frames
- B64C1/1461—Structures of doors or surrounding frames
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1407—Doors; surrounding frames
- B64C1/1469—Doors between cockpit and cabin
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- Aviation & Aerospace Engineering (AREA)
- Body Structure For Vehicles (AREA)
- Joining Of Building Structures In Genera (AREA)
Abstract
The invention provides a cockpit entrance and exit portal frame structure and a design method thereof, wherein the portal frame structure is arranged at a position of a required opening on a floor panel and comprises a portal frame (1), a machine corner box joint (2) and a diaphragm plate (4); the mouth frame (1) is a sectional type surrounding frame and comprises a longitudinal reinforcing beam and a transverse reinforcing beam with I-shaped sections; the sectional type enclosing frames are arranged on the periphery of the door body in a groined shape, the enclosing frames are butted into an integral opening frame through the machine corner box joints, the door body is embedded in the inner periphery of the groined opening frame through the hinge joints, and the opening frame is connected with the floor panel through bolts; a plurality of transverse partition plates (4) which are parallel to each other are arranged along the longitudinal direction at the periphery of the # -shaped opening frame, and the transverse partition plates (4) are simultaneously connected with the floor panel through rivets. The mouth frame structure adopts a combination form of the sectional surrounding frame and the machined corner box, so that the rigidity requirement of the mouth frame of the surrounding structure is met, the processing manufacturability is improved, and the manufacturing cost is reduced.
Description
Technical Field
The invention belongs to the field of aircraft cockpit, and particularly relates to a cockpit entrance and exit door frame structure and a design method thereof.
Background
In order to meet the usability requirements of the aircraft, openings are required to be arranged on the aircraft. Aircraft structure opening forms are generally of three types: small openings for observation windows and oil filling openings. The integrity of a bearing structure is not damaged, the periphery of an opening is reinforced by a cushion plate in a frame mode, and the opening is covered by a quick-release screw cap; the middle-sized opening for system maintenance destroys the integrity of the stressed components of the fuselage, and needs a bearing opening cover which is connected with the stressed components of the opening structure into a whole. The mouth cover is fixed on the force bearing component along the periphery of the opening by using screws to ensure that the mouth frame and the skin are jointly sheared (when being twisted) or tensioned (when being bent); the large openings for the access door of the cockpit, the cabin door of the cargo hold, the cabin door of the landing gear and the like are generally limited by conditions, and can not adopt a bearing opening cover connected with a stressed structure of the body, and the rigidity reinforcement design needs to be carried out on an opening frame.
The access door of the aircraft cockpit belongs to a cabin door in the aircraft body, is a bridge channel for connecting the cockpit and a cargo hold or a passenger cabin, and needs to consider the integral hoisting requirement of kitchen equipment, the opening mode of the cabin door and the requirements of a mechanism for door opening operation and an air spring. The size of the opening is larger, so that the main force transmission structure part in the area is weakened and interrupted, and meanwhile, the opening also causes local stress concentration in the area of the opening, so that the overall force transmission and rigidity of the machine body structure are greatly influenced. The entrance and exit door frame generally takes the form of an integral frame or a combined frame. The whole mouth frame has good rigidity performance, is beneficial to bearing, but has large processing difficulty and poor economical efficiency.
Disclosure of Invention
It is an object of the present invention to provide a cockpit access door frame structure and method of designing the same that overcomes or alleviates at least one of the above-mentioned deficiencies of the prior art.
The purpose of the invention is realized by the following technical scheme: a cockpit entrance and exit portal frame structure is arranged at a position of a floor panel where an opening is required, and comprises a portal frame, a machine corner box joint and a transverse clapboard; the mouth frame is a sectional type surrounding frame and comprises a longitudinal reinforcing beam and a transverse reinforcing beam with I-shaped sections; the sectional type enclosing frames are arranged on the periphery of the door body in a groined shape, the enclosing frames are butted into an integral opening frame through the machine corner box joints, the door body is embedded in the inner periphery of the groined opening frame through the hinge joints, and the opening frame is connected with the floor panel through bolts; a plurality of transverse partition plates which are parallel to each other are arranged along the longitudinal direction at the periphery of the # -shaped opening frame, and the transverse partition plates are simultaneously connected with the floor panel through rivets.
Preferably, the hinge joint is mounted using a plurality of bolts arranged side by side.
Preferably, the edge strip and the extension section in the opening frame are connected with the floor panel by using double rows of bolts, wherein the bolts connected between the opening frame edge strip and the floor panel are high-locking bolts.
Preferably, the butt joint of the mouth frame comprises the connection of a web plate and a flange strip, the butt joint of the mouth frame forms cross four-corner connection, the mouth frame web plate is connected with a three-side corner box and an L-shaped corner piece back to back through self reinforcement, and the mouth frame web plate is connected with the corner piece and the corner box through double rows of high-lock bolts; the edge strips are connected through cross corner pieces, and the connecting pieces are double rows of high locking bolts.
Preferably, the diaphragm is connected to the floor panel with a single row of rivets.
Preferably, a longitudinal beam is arranged between the two longitudinal reinforcing beams at the periphery of the groined-shaped mouth frame.
A design method of a cockpit entrance and exit door frame structure comprises the following steps,
the method comprises the following steps: arranging a transverse stiffening beam and a longitudinal stiffening beam which are arranged in a groined shape at the opening position of the floor panel;
step two: butt joint among stiffening beams of the groined-shaped opening frame;
step three: calculating the cross section sizes of the transverse reinforcing beam and the longitudinal reinforcing beam;
step four: the door body is connected with the mouth frame stiffening beam through a hinge joint;
step five: the floor panel is connected with the opening frame edge strip through double rows of high-lock bolts;
step six: the opening frame extension sections are connected;
step seven: and connecting the diaphragm plates.
Preferably, in the second step, the mouth frame butt joint comprises the connection of a web plate and inner edges, the cross-shaped four-corner connection is formed at the mouth frame butt joint part, the web plate is connected with a three-corner box and an L-shaped corner piece back to back through self reinforcement, the mouth frame web plate is connected with the corner piece and the corner box by using double rows of high locking bolts and then connected to the web plate, the inner edges are connected through the cross-shaped corner piece, and the connecting piece is a double row of high locking bolts;
the double rows of bolts on the opening frame bear the shearing load, the frame web plate is high h, and the working shearing force on the bolts is calculated according to the most serious condition of coupling of the positive stress sigma and the shearing stress tau on the opening frame web plate
Shear force of bolt failure is [ P ]s]The bolt shear safety margin is
The bolt hole crush failure load is
[Pbr]＝d0×δ×kbr×σb
Wherein d is0For the diameter of the bolt used, δ is the thickness of the interlayer, kbrTaking delta as the thickness of the corner box with three sides as the extrusion coefficient, and taking the extrusion coefficient kbr＝1.8；
Working extrusion force PbrEqual to the working shear force on the bolt, the extrusion safety margin of the bolt hole is
The double-row bolts connected between the mouth frame web plates bear the combined action of tensile force and shearing force, and the tensile-shearing margin of the bolts is calculated by taking the maximum positive stress sigma and the maximum shearing stress tau on the connecting web plates and the maximum axial stress sigma' on the outer edges;
the working tension of the single bolt
Working shear force of single bolt
Bolt breaking tension [ P ]t]Shear force of single-side failure is [ P ]s]The shear safety margin of the bolt is
The bolt connection on the inner edge of the opening frame is calculated according to the shearing strength of the bolt and the extrusion strength of the bolt hole, the width b and the thickness delta of the inner edge, and the working shearing force on the bolt is calculated according to the maximum axial stress sigma on the inner edge of the opening frame
Shear force of bolt failure is [ P ]s]The bolt shear safety margin is
The bolt hole crush failure load is
[Pbr]＝d0×δ×kbr×σb
Wherein d is0For the diameter of the bolt used, δ is the thickness of the interlayer, kbrTaking delta as the thickness of the cross-shaped angle piece as the extrusion coefficient, and taking the extrusion coefficient kbr＝1.8；
Working extrusion force PbrEqual to the working shear force on the bolt, the extrusion safety margin of the bolt hole is
In the fourth step, the hinge joint is a plurality of bolts arranged side by side, and the breaking tension of the bolts is [ P ]t]Shear force of single-side failure is [ P ]s]The hinge joint obtains the maximum working tension P under the airtight working conditiontMaximum working shear force PsThe tensile safety margin of the connecting bolt is
The shear safety margin of the bolt is
The bolt hole crush failure load is
[Pbr]＝d0×δ×kbr×σb
Wherein d is0Is the bolt diameter, delta is the interlayer thickness, kbrTaking delta as the sum of the thicknesses of the mouth frame and the reinforcing backing plate, namely delta, and taking the material strength limit sigma as an extrusion coefficientbCoefficient of extrusion kbr＝1.8；
Working extrusion force PbrEqual to the working shear force on the bolt, the extrusion safety margin of the bolt hole is
In the fifth step, the connection strength of the bolts is calculated according to the shearing strength of the bolts and the extrusion strength of the bolt holes, the most serious coupling condition of the positive stress sigma and the shearing stress tau of the floor panel at the joint is taken to calculate the connection strength of the bolts,
the natural grid width of the floor panel is b, the number of double-row bolts is n, and the shearing force borne by a single bolt is
Shear force of single-side failure of bolt is [ P ]s]The bolt shear safety margin is
The bolt hole crush failure load is
[Pbr]＝d0×δ×kbr×σb
Wherein d is0Is the bolt diameter, delta is the interlayer thickness, kbrTaking delta as the thickness of the skin and the reinforced cushion plate as the extrusion coefficient, and taking the extrusion coefficient kbr＝1.8；
Working extrusion force PbrEqual to the working shear force on the bolt, the extrusion safety margin of the bolt hole
In the sixth step, the extension sections of the opening frames are connected by double rows of bolts, the distance between the bolts is l, and the maximum shear flow difference q of the floor panel at the joint is taken to calculate the working shear force on the bolts
Shear force of bolt failure is [ P ]s]The bolt shear safety margin is
The bolt hole crush failure load is
[Pbr]＝d0×δ×kbr×σb
Wherein d is0Is the bolt diameter, delta is the interlayer thickness, kbrTaking delta as the thickness of the skin and the reinforced cushion plate as the extrusion coefficient, and taking the extrusion coefficient kbr＝1.8；
Working extrusion force PbrEqual to the working shear force on the bolt, the extrusion safety margin of the bolt hole
Step seven, the diaphragm plate is connected with the floor panel by using a single row of rivets, the maximum shear flow difference q of the joint of the floor panel is taken to calculate the strength of rivet connection, the thickness delta of the joint and the maximum interval l are calculated, and the working shear force on the rivets is
Ps＝ql
Shear force of rivet failure is [ P ]s]Shear safety margin of the rivet
The working extrusion force of the rivet hole is equal to the working shear force of the rivet, and the destructive extrusion force [ P ] of the rivet holebr]And rivet hole extrusion safety margin:
the cockpit entrance and exit portal frame structure and the design method thereof have the advantages that the combination of the segmented surrounding frame and the machined corner box is adopted, so that the rigidity requirement of the surrounding portal frame is met, the processing manufacturability is improved, and the manufacturing cost is reduced.
Drawings
FIG. 1 is a schematic structural view of an entrance/exit structure of a cockpit according to the present invention;
FIG. 2 is a schematic view of the installation of a shaft-shaped stiffening beam in the entrance/exit structure of the cockpit according to the present invention;
FIG. 3 is a simplified schematic view of a reinforcing beam loaded in the structure of the entrance/exit door of the cockpit according to the present invention;
FIG. 4 is a schematic view illustrating the stress and deformation of a reinforcing beam in the entrance/exit structure of the cockpit according to the present invention;
FIG. 5 is a schematic cross-sectional view of a reinforcing beam in the structure of the entrance/exit door of the cockpit according to the present invention;
fig. 6 is a schematic view showing the installation of the structure of the entrance/exit door of the cockpit according to the present invention.
Reference numerals:
1-opening frame, 2-machine angle box joint, 3-longitudinal beam and 4-diaphragm plate.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The present invention will be described in further detail with reference to the accompanying drawings.
As shown in fig. 1 and 6, a cockpit access door frame structure is arranged at a position of a floor panel where an opening is required, and comprises a door frame 1, a corner box joint 2 and a diaphragm plate 4. The mouth frame 1 is a sectional type surrounding frame and comprises a longitudinal reinforcing beam and a transverse reinforcing beam with I-shaped sections. This sectional type encloses the frame and is the groined type and arranges peripherally at the door body, each encloses and connects the butt joint through machine adding the angle box between the frame and be a whole mouthful frame, the butt joint of mouthful frame includes the connection of web and flange, mouthful frame butt joint department forms cross four corners connection, mouthful frame web is connected back to back through self add muscle and trilateral angle box and L shape angle piece, wherein mouthful frame web and angle piece, the angle box uses double high lock bolted connection, the flange is connected through cross angle piece, the connecting piece is double high lock bolted connection. The door body is embedded in the inner periphery of the groined-shaped opening frame through a hinge joint, and the hinge joint is installed by adopting a plurality of bolts arranged side by side. The opening frame is connected with the floor panel through bolts, the edge strip and the extension section in the opening frame are connected with the floor panel through double rows of bolts, and the bolts connected between the opening frame edge strip and the floor panel are high-locking bolts. A plurality of transverse clapboards 4 which are parallel to each other are arranged on the periphery of the groined-shaped opening frame along the longitudinal direction, the transverse clapboards 4 are connected with a floor panel through single-row rivets, and a longitudinal beam 3 is arranged between two longitudinal reinforcing beams on the periphery of the groined-shaped opening frame.
The method for designing the structure of the entrance and exit door frame of the cockpit of the present invention is described as follows,
(1) the floor is characterized in that a transverse reinforcing beam and a longitudinal reinforcing beam which are arranged in a groined shape are arranged at the opening position of the floor panel. (2) And the reinforcing beams of the groined-shaped frame 1 are butted. (3) And calculating the cross-sectional dimensions of the transverse reinforcing beam and the longitudinal reinforcing beam. (4) The door body is connected with the reinforcing beam of the mouth frame 1 through a hinge joint. (5) The floor panel is connected with the opening frame 1 edge strip through double rows of high-lock bolts. (6) The opening frame 1 is connected with an extension section.
(7) And connecting the diaphragm plates 4.
The steps are explained in detail below.
The method comprises the following steps: the floor panel is provided with a transverse stiffening beam and a longitudinal stiffening beam which are arranged in a groined shape at the opening position, as shown in figure 2.
Step two: and the reinforcing beams of the groined-shaped frame 1 are butted.
The port frame butt joint comprises the connection of a web plate and inner edges, the cross four-corner connection is formed at the butt joint of the port frames, the web plate is connected with a three-corner box and an L-shaped corner piece back to back through self reinforcement, the port frame web plate is connected with the corner piece and the corner box by using double rows of high locking bolts and then connected to the web plate, the inner edges are connected through the cross corner piece, and the connecting piece is a double row of high locking bolts;
the double rows of bolts on the opening frame bear the shearing load, the frame web plate is high h, and the working shearing force on the bolts is calculated according to the most serious condition of coupling of the positive stress sigma and the shearing stress tau on the opening frame web plate
Shear force of bolt failure is [ P ]s]The bolt shear safety margin is
The bolt hole crush failure load is
[Pbr]＝d0×δ×kbr×σb
Wherein d is0For the diameter of the bolt used, δ is the thickness of the interlayer, kbrTaking delta as the thickness of the corner box with three sides as the extrusion coefficient, and taking the extrusion coefficient kbr＝1.8；
Working extrusion force PbrEqual to the working shear force on the bolt, the extrusion safety margin of the bolt hole is
The double-row bolts connected between the mouth frame web plates bear the combined action of tensile force and shearing force, and the tensile-shearing margin of the bolts is calculated by taking the maximum positive stress sigma and the maximum shearing stress tau on the connecting web plates and the maximum axial stress sigma' on the outer edges;
the working tension of the single bolt
Working shear force of single bolt
Bolt breaking tension [ P ]t]Shear force of single-side failure is [ P ]s]The shear safety margin of the bolt is
The bolt connection on the inner edge of the opening frame is calculated according to the shearing strength of the bolt and the extrusion strength of the bolt hole, the width b and the thickness delta of the inner edge, and the working shearing force on the bolt is calculated according to the maximum axial stress sigma on the inner edge of the opening frame
Shear force of bolt failure is [ P ]s]The bolt shear safety margin is
The bolt hole crush failure load is
[Pbr]＝d0×δ×kbr×σb
Wherein d is0For the diameter of the bolt used, δ is the thickness of the interlayer, kbrTaking delta as the thickness of the cross-shaped angle piece as the extrusion coefficient, and taking the extrusion coefficient kbr＝1.8；
Working extrusion force PbrEqual to the working shear force on the bolt, the extrusion safety margin of the bolt hole is
Step three: and calculating the cross-sectional dimensions of the transverse reinforcing beam and the longitudinal reinforcing beam.
According to the force transmission characteristic, the reinforcing beam can be simplified into a double-fulcrum beam model which bears uniformly distributed loads and is fixedly supported at two ends, as shown in figure 3, and the stress sketch is as shown in figure 4.
According to the engineering beam theory, the length l of the reinforcing beam, the uniform load q born by the reinforcing beam, the maximum shearing force and bending moment on the longitudinal beam are as follows:
the maximum bending stress on the longitudinal beam is as follows:
the cross section of the I-shaped reinforcing beam is determined by calculation, and the cross section is shown in figure 5.
Step four: the door body is connected with the reinforcing beam of the mouth frame 1 through a hinge joint.
The cockpit access door is connected to the door frame by a hinge joint, and the connecting piece is a plurality of bolts side by side. Of boltsBreaking tension of [ P ]t]Shear force of single-side failure is [ P ]s]The hinge joint obtains the maximum working tension P under the airtight working conditiontMaximum working shear force PsThe tensile safety margin of the connecting bolt is
The shear safety margin of the bolt is
The bolt hole crush failure load is
[Pbr]＝d0×δ×kbr×σb
Wherein d is0Is the bolt diameter, delta is the interlayer thickness, kbrIn order to obtain the extrusion factor,
taking delta as the sum of the thicknesses of the mouth frame and the reinforcing cushion plate, namely delta, and taking the material strength limit sigmabCoefficient of extrusion
kbr＝1.8；
Working extrusion force PbrEqual to the working shear force on the bolt, the extrusion safety margin of the bolt hole is
Step five: the floor panel is connected with the opening frame 1 edge strip through double rows of high-lock bolts.
The floor panel at the opening frame is connected with the opening frame edge strip by adopting double rows of bolts which are all high locking bolts. The connection strength of the bolts is calculated according to the shearing strength of the bolts and the extrusion strength of the bolt holes, the connection strength of the bolts is calculated according to the most serious condition of coupling of the positive stress sigma and the shearing stress tau of the floor panels at the connection part,
the natural grid width of the floor panel is b, the number of double-row bolts is n, and the shearing force borne by a single bolt is
Shear force of single-side failure of bolt is [ P ]s]The bolt shear safety margin is
The bolt hole crush failure load is
[Pbr]＝d0×δ×kbr×σb
Wherein d is0Is the bolt diameter, delta is the interlayer thickness, kbrTaking delta as the thickness of the skin and the reinforced cushion plate as the extrusion coefficient, and taking the extrusion coefficient kbr＝1.8；
Working extrusion force PbrEqual to the working shear force on the bolt, the extrusion safety margin of the bolt hole
Step six: the opening frame 1 is connected with an extension section.
The extension section of the opening frame is connected by double rows of bolts with the distance of l, and the maximum shear difference q of the floor panel at the joint is taken to calculate the working shear on the bolts
Shear force of bolt failure is [ P ]s]The bolt shear safety margin is
The bolt hole crush failure load is
[Pbr]＝d0×δ×kbr×σb
Wherein d is0Is the bolt diameter, delta is the interlayer thickness, kbrTaking delta as the thickness of the skin and the reinforced cushion plate as the extrusion coefficient, and taking the extrusion coefficient kbr＝1.8；
Working extrusion force PbrEqual to the working shear force on the bolt, the extrusion safety margin of the bolt hole
Step seven: and connecting the diaphragm plates 4.
Step seven, the diaphragm plate is connected with the floor panel by using a single row of rivets, the maximum shear flow difference q of the joint of the floor panel is taken to calculate the strength of rivet connection, the thickness delta of the joint and the maximum interval l are calculated, and the working shear force on the rivets is
Ps＝ql
Shear force of rivet failure is [ P ]s]Shear safety margin of the rivet
The working extrusion force of the rivet hole is equal to the working shear force of the rivet, and the destructive extrusion force [ P ] of the rivet holebr]And rivet hole extrusion safety margin:
the above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (1)
1. A design method of a cockpit entrance and exit portal frame structure is characterized in that,
the cockpit entrance and exit portal frame structure comprises a portal frame (1), a corner box joint (2) and a diaphragm plate (4); the mouth frame (1) is a sectional type surrounding frame and comprises a longitudinal reinforcing beam and a transverse reinforcing beam with I-shaped sections; the sectional type enclosing frames are arranged on the periphery of the door body in a groined shape, the enclosing frames are butted into an integral opening frame through the machine corner box joints, the door body is embedded in the inner periphery of the groined opening frame through the hinge joints, and the opening frame is connected with the floor panel through bolts; a plurality of transverse partition plates (4) which are parallel to each other are arranged on the periphery of the groined-shaped opening frame along the longitudinal direction, and the transverse partition plates (4) are connected with the floor panel through rivets at the same time;
the hinge joint is installed by adopting a plurality of bolts arranged side by side;
the edge strip and the extension section in the opening frame are connected with the floor panel by adopting double rows of bolts, wherein the bolts connected between the opening frame edge strip and the floor panel are high-locking bolts;
the butt joint of the mouth frames comprises the connection of a web plate and a flange strip, the butt joint of the mouth frames forms cross four-corner connection, the mouth frame web plate is connected with a three-side corner box and an L-shaped corner piece back to back through self reinforcement, and the mouth frame web plate is connected with the corner piece and the corner box through double rows of high-lock bolts; the edge strips are connected through cross corner pieces, and the connecting pieces are double rows of high locking bolts;
the diaphragm plate (4) is connected with the floor panel by adopting a single row of rivets;
the design method of the cockpit entrance and exit portal frame structure comprises the following steps:
the method comprises the following steps: arranging a transverse stiffening beam and a longitudinal stiffening beam which are arranged in a groined shape at the opening position of the floor panel;
step two: butt joint among stiffening beams of the groined-shaped frame (1);
step three: calculating the cross section sizes of the transverse reinforcing beam and the longitudinal reinforcing beam;
step four: the door body is connected with the reinforcing beam of the opening frame (1) through a hinge joint;
step five: the floor panel is connected with the edge strip of the opening frame (1) through double rows of high-lock bolts;
step six: the opening frame (1) is connected with the extending section;
step seven: the diaphragm plates (4) are connected;
step two, the butt joint of the opening frames comprises the connection of a web plate and inner edges, the butt joint of the opening frames forms cross four-corner connection, the web plate is connected with a three-corner box and an L-shaped corner piece back to back through self reinforcement, the web plate of the opening frames is connected with the corner piece and the corner box by using double rows of high locking bolts and then connected to the web plate, the inner edges are connected through the cross corner piece, and the connecting piece is a double row of high locking bolts;
the double rows of bolts on the opening frame bear the shearing load, the frame web plate is high h, and the working shearing force on the bolts is calculated according to the most serious condition of coupling of the positive stress sigma and the shearing stress tau on the opening frame web plate
Shear force of bolt failure is [ P ]s]The bolt shear safety margin is
The bolt hole crush failure load is
[Pbr]＝d0×δ×kbr×σb
Wherein d is0For the diameter of the bolt used, δ is the thickness of the interlayer, kbrTaking delta as the thickness of the corner box with three sides as the extrusion coefficient, and taking the extrusion coefficient kbr＝1.8；
Working extrusion force PbrEqual to the working shear force on the bolt, the extrusion safety margin of the bolt hole is
The double-row bolts connected between the mouth frame web plates bear the combined action of tensile force and shearing force, and the tensile-shearing margin of the bolts is calculated by taking the maximum positive stress sigma and the maximum shearing stress tau on the connecting web plates and the maximum axial stress sigma' on the outer edges;
the working tension of the single bolt
Working shear force of single bolt
Bolt breaking tension [ P ]t]Shear force of single-side failure is [ P ]s]The shear safety margin of the bolt is
The bolt connection on the inner edge of the opening frame is calculated according to the shearing strength of the bolt and the extrusion strength of the bolt hole, the width b and the thickness delta of the inner edge, and the working shearing force on the bolt is calculated according to the maximum axial stress sigma on the inner edge of the opening frame
Shear force of bolt failure is [ P ]s]The bolt shear safety margin is
The bolt hole crush failure load is
[Pbr]＝d0×δ×kbr×σb
Wherein d is0Depending on the diameter of the bolt used,delta is the interlayer thickness, kbrTaking delta as the thickness of the cross-shaped angle piece as the extrusion coefficient, and taking the extrusion coefficient kbr＝1.8；
Working extrusion force PbrEqual to the working shear force on the bolt, the extrusion safety margin of the bolt hole is
In the fourth step, the hinge joint is a plurality of bolts arranged side by side, and the breaking tension of the bolts is [ P ]t]Shear force of single-side failure is [ P ]s]The hinge joint obtains the maximum working tension P under the airtight working conditiontMaximum working shear force PsThe tensile safety margin of the connecting bolt is
The shear safety margin of the bolt is
The bolt hole crush failure load is
[Pbr]＝d0×δ×kbr×σb
Wherein d is0Is the bolt diameter, delta is the interlayer thickness, kbrIn order to obtain the extrusion factor,
taking delta as the sum of the thicknesses of the mouth frame and the reinforcing cushion plate, namely delta, and taking the material strength limit sigmabCoefficient of extrusion kbr＝1.8；
Working extrusion force PbrEqual to the working shear force on the bolt, the extrusion safety margin of the bolt hole is
In the fifth step, the connection strength of the bolts is calculated according to the shearing strength of the bolts and the extrusion strength of the bolt holes, the most serious coupling condition of the positive stress sigma and the shearing stress tau of the floor panel at the joint is taken to calculate the connection strength of the bolts,
the natural grid width of the floor panel is b, the number of double-row bolts is n, and the shearing force borne by a single bolt is
Shear force of single-side failure of bolt is [ P ]s]The bolt shear safety margin is
The bolt hole crush failure load is
[Pbr]＝d0×δ×kbr×σb
Wherein d is0Is the bolt diameter, delta is the interlayer thickness, kbrTaking delta as the thickness of the skin and the reinforced cushion plate as the extrusion coefficient, and taking the extrusion coefficient kbr＝1.8；
Working extrusion force PbrEqual to the working shear force on the bolt, the extrusion safety margin of the bolt hole
In the sixth step, the extension sections of the opening frames are connected by double rows of bolts, the distance between the bolts is l, and the maximum shear flow difference q of the floor panel at the joint is taken to calculate the working shear force on the bolts
Bolt failure shearIs [ P ]s]The bolt shear safety margin is
The bolt hole crush failure load is
[Pbr]＝d0×δ×kbr×σb
Wherein d is0Is the bolt diameter, delta is the interlayer thickness, kbrTaking delta as the thickness of the skin and the reinforced cushion plate as the extrusion coefficient, and taking the extrusion coefficient kbr＝1.8；
Working extrusion force PbrEqual to the working shear force on the bolt, the extrusion safety margin of the bolt hole
Step seven, the diaphragm plate is connected with the floor panel by using a single row of rivets, the maximum shear flow difference q of the joint of the floor panel is taken to calculate the strength of rivet connection, the thickness delta of the joint and the maximum interval l are calculated, and the working shear force on the rivets is
Ps＝ql
Shear force of rivet failure is [ P ]s]Shear safety margin of the rivet
The working extrusion force of the rivet hole is equal to the working shear force of the rivet, and the destructive extrusion force [ P ] of the rivet holebr]And rivet hole extrusion safety margin:
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