CN110466801B - Aircraft cabin structure - Google Patents
Aircraft cabin structure Download PDFInfo
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- CN110466801B CN110466801B CN201910441174.4A CN201910441174A CN110466801B CN 110466801 B CN110466801 B CN 110466801B CN 201910441174 A CN201910441174 A CN 201910441174A CN 110466801 B CN110466801 B CN 110466801B
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- inclined strut
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
Abstract
The invention discloses an aircraft cabin structure, which has the functions of participating in maintaining the configuration of an aircraft or a spacecraft, providing a rotating shaft mounting interface of an external swinging element of a cabin, providing a mounting interface of a driving device of the swinging element and bearing the mechanical load generated by the swinging element. The cabin body consists of a cabin section and a combined support, the cabin section is a semi-hard shell with a transverse reinforcing frame and a vertical reinforcing rib, and a reinforcing joint is arranged below the combined support; the combined support comprises a wall plate, a column body, a corner support, a diagonal support and a reinforcing plate, wherein the wall plate and the column body provide an external element mounting interface and bear and transmit external loads together with the corner support and the diagonal support. The invention solves the problems that the cabin section is acted by lateral concentrated force, and the local rigidity and the strength are insufficient, and provides a mechanical interface and a bearing structure for the swinging component.
Description
Technical Field
The invention relates to an aircraft cabin structure, in particular to a cabin which adopts a semi-hard shell cabin section, bears a large concentrated force load outside the cabin and provides a mechanical interface and a mechanical interface for an external swinging component.
Background
The common aircraft or spacecraft cabin is usually of a semi-hard shell structure, mainly bears uniformly distributed loads along the axial direction of the cabin, has high strength and rigidity along the axial direction, and has poor capability of bearing radial concentrated force.
There are two technical solutions for the currently available cabin with external oscillating/rotating parts:
first, a semi-hard shell hull enclosure + low load swing/swivel components is used. In this case, the joint between the root of the rotating or oscillating member and the nacelle is generally reinforced by thin-walled parts with small radial dimensions, and the nacelle is still poor in capability of bearing radial concentrated forces, which requires the oscillating member to have a small mass or inertia to avoid the nacelle from being damaged by the large concentrated force load. The manned spacecraft propulsion cabin and the solar wing are common cases.
Second, a hard shell hull + heavy load swing/swivel components are used. In this case, the hard shell cabin body is generally made of steel, the structural mass of the hard shell cabin body is greatly increased, the structural efficiency is low, and the hard shell cabin body meets the bearing requirement of a large-load swinging/rotating component outside the cabin, but is only suitable for a small-diameter solid rocket which is made of steel or other carriers which do not make requirements on weight. The application cases of the scheme are generally ballistic missile tail sections with movable empennages or grid rudders and the secondary sections of the falcon rockets of the overseas space X company.
In summary, when a large load swing component, such as a grid rudder or other large inertia payload, which is subjected to airflow scouring in the atmosphere, needs to be installed on the outer side of the semi-hard shell cabin body, and there is a high requirement for structural efficiency, both of the above two schemes cannot be satisfied.
At present, no relevant technical instruction or report of the cabin section adopting the semi-hard shell and the cabin body with the mechanical interface and the mechanical interface of the swinging component is found, and similar data at home and abroad are not collected.
Therefore, research is carried out on the semi-hard shell cabin body bearing the radial concentrated force load so as to meet the installation and bearing requirements of the swing component outside the cabin.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the aircraft cabin structure is disclosed, the problems of insufficient local rigidity and strength under the action of lateral concentrated force generated by a large-load swinging component on a semi-hard shell cabin section are solved, and meanwhile, an installation interface and a bearing structure are provided for the swinging component.
The technical scheme adopted by the invention for realizing the purpose is as follows: an aircraft cabin structure comprises a cabin section and at least one combined support; the cabin section is a semi-hard shell with a transverse reinforcing frame and a vertical reinforcing rib; the combined support is positioned at the inner side of the cabin section, and a reinforced joint is arranged below the combined support;
the combination support contains wallboard, cylinder, gusset, first bracing, second bracing, reinforcing plate, and the wallboard constitutes the major structure of combination support with the cylinder, strengthens through each gusset, first bracing, second bracing, reinforcing plate, wherein:
the upper surface of the wall plate is connected with the upper reinforcing frame of the cabin section, the lower surface of the wall plate is connected with the lower reinforcing frame of the cabin section, and one side of the wall plate, which is close to the cabin section, is provided with a groove-shaped notch connected with a reinforcing rib; the wall plate provides a driving device interface;
the column body is fastened and connected with the wall plate through a screw, a nut, a washer and a threaded hole on the wall plate; the cylinder is hollow, and a bearing and a rotating shaft of the swinging component are arranged;
the angle braces are positioned at four corners of the wall plate, vertical flanges in each angle brace part are connected with the side surface of the wall plate, and horizontal flanges in each angle brace part are connected with the reinforcing frame;
one end of the first inclined strut and one end of the second inclined strut are connected with the inner corner of the wall plate, and the other ends of the first inclined strut and the second inclined strut are connected with the side face of the column body;
one end of the reinforcing plate is connected with the inner side of the wall plate, and the other end of the reinforcing plate is connected with the column body;
the combined support forms an installation space by a wall plate, a column body and a reinforcing plate and is used for installing a driving device for driving the swinging component to swing.
The outer surface of the wall plate is provided with a groove-shaped notch, the groove-shaped notch is matched with the corresponding reinforcing rib, and the groove-shaped notch penetrates through or does not penetrate through the wall plate structure;
the wall plate is provided with a circular through hole for the rotating shaft to pass through, the circular through hole is matched with the cylinder cavity, a flange mounting surface is arranged by taking the circular through hole as the center, bolt holes are axially and uniformly distributed, a solid area below the circular through hole is provided with a threaded hole, the bolt holes and the threaded holes are used for being connected with the cylinder, and a nut mounting groove is arranged at the position of the outer surface of the wall plate corresponding to the bolt holes; a boss is arranged on the inner surface far away from the circular through hole and at the same horizontal height, and a pin hole is formed in the boss and used for being connected with a tailstock of the driving device;
reinforcing ribs are arranged by taking the circular through hole as the circle center, the radial reinforcing ribs point to the four corners of the wall plate, and horizontal reinforcing ribs are arranged between the circular through hole and the pin holes; and an outer bearing mounting step is arranged on the outward side of the circular through hole.
The cylinder is of a hollow cylindrical structure with a flange, wherein the flange is matched with the flange on the wall plate; a notch along the circumferential direction is formed on the cylinder body close to the flange, a crank in the rotating shaft part is allowed to extend out and provide a certain swinging space, and the extending end of the crank is connected with a driving device; the end surface of the cylinder body is provided with a threaded hole for connecting with a bearing end cover of the rotating shaft, and the outer surface of the end surface of the cylinder body is provided with a threaded hole for connecting with the inclined strut and the reinforcing plate; the outer surface of the cylinder is provided with weight reduction grooves which are distributed circumferentially; the inner body of the hollow cavity of the cylinder is provided with an inner side bearing mounting step and a crank positioning step. The lower end of the column body is provided with a small plane which is flush with the lower surface of the wall plate.
Circular through-hole and cylinder cavity have constituted the cylindrical cavity of series connection jointly for hold the pivot, wherein the cavity is close to wallboard one end and has bearing installation step to be used for installing pivot outside bearing, and the cavity is close to cylinder one end and has bearing installation step for installing pivot inside bearing, forms two face of cylinder diameters D1, D2 of bearing installation step to and the straight D3 of two face of cylinder that form bearing installation step, D4.
(D1-D2)/2＜δ1，
(D3-D4)/2＜δ2，
Wherein δ 1 is the outer ring thickness of the outer bearing of the rotating shaft, and δ 2 is the outer ring thickness of the inner bearing of the rotating shaft.
Among the combination support, cylinder diameter D0, the distance C1 of cylinder circumference breach middle surface and wallboard horizontal strengthening rib, cylinder breach middle surface and cylinder terminal surface distance C2, cylinder axis and wallboard left side edge axis distance L1, cylinder axis and pinhole axis distance L2, cylinder axis distance wallboard lower terminal surface distance H1, cylinder axis distance wallboard up end distance H2 and first bracing and cylinder axis contained angle alpha, second bracing and cylinder axis contained angle beta, reinforcing plate angle of inclination gamma satisfies the following relation:
the gap (402) is offset by an angle δ satisfying:
wherein L is0The initial length of the drive in the zero position.
Each corner support is composed of a horizontal flanging and a vertical flanging, a reinforcing rib is arranged between the flanging, the horizontal flanging is in matched connection with the cabin section reinforcing frame in an arched manner, and the vertical flanging is in matched connection with the side wall of the wall plate in a rectangular manner.
The first inclined strut and the second inclined strut are of a space structure, one end of each first inclined strut is an L-shaped joint, the other end of each first inclined strut is an arc-shaped joint, and the two ends of each first inclined strut and the two ends of each second inclined strut are connected into a whole through a middle connecting beam; the L-shaped joint is connected with the upper left corner of the wallboard, and the second inclined strut L-shaped joint is connected with the lower left corner of the wallboard; the included angles alpha and beta between the first inclined strut and the column axis and between the second inclined strut and the column axis are all in the range of 30-45 degrees.
One end of the reinforcing plate is a cylindrical surface flanging and is connected with the cylinder, the other end of the reinforcing plate is a plane flanging with a notch, a floating nut is installed on the inner side of the plane flanging, the plane flanging is installed on the inner side of the right wall of the wallboard, and the reinforcing plate and the wallboard are connected together through a screw penetrating through the outer side.
The cabin section and the combined support are made of metal or fiber composite materials or combination of metal and fiber composite materials.
The connection mode among the wallboard, the column body, the corner brace, the first inclined brace, the second inclined brace and the reinforcing plate adopts screw connection or rivet connection or glue solution bonding.
Compared with the prior art, the invention has the following advantages and beneficial effects:
1. according to the invention, by adopting the scheme that the combined support is additionally arranged on the inner wall of the semi-hard shell cabin section, the local previous capability of the semi-hard shell cabin section is improved, the problem that a large-load swinging component cannot be arranged outside the cabin in the conventional semi-hard shell cabin section is solved, the structural efficiency of the aircraft cabin section is improved, and the functional expansion of the conventional aircraft cabin body is facilitated;
2. according to the invention, the wallboard is additionally arranged on the inner side of the semi-hard shell cabin section, the reinforcing frames are arranged above and below the wallboard, and the wallboard and the reinforcing frames are connected through the corner support part, so that the wallboard part and the reinforcing frames are connected into a whole, and the local rigidity and strength of the semi-hard shell cabin section are improved;
3. according to the invention, the wall plate with the round hole and the cylinder part are additionally arranged in the semi-hard shell cabin section to form the serially connected cylindrical cavity, so that the rotating shaft of the external swinging component can be accommodated, and the installation of the large-size external swinging component on the semi-hard shell cabin section is facilitated;
4. according to the invention, the reinforcing ribs are arranged on the inner surface of the wall plate, and the inclined strut parts are arranged between the column body and the wall plate, so that a simple and effective load transmission path is formed between the rotating shaft of the external swinging part and the semi-hard shell cabin section, and external large load is effectively and safely transmitted and dispersed to the reinforced semi-hard shell cabin section;
5. according to the invention, through the layout design of the combined support, enough installation space is formed among the wall plate, the column body and the reinforcing plate, the swinging component driving device can be accommodated, a power source and support counterforce are provided for the swinging of the swinging component, and the normal function of the swinging component outside the cabin body is ensured.
In conclusion, the semi-hard shell cabin solves the problems that the semi-hard shell cabin is subjected to lateral concentrated force and has insufficient local rigidity and strength, provides the installation space and the interface of an external swinging component (comprising a driving device), and is beneficial to expanding the application field of aircrafts or spacecrafts.
Drawings
FIG. 1 is a schematic view of an aircraft or spacecraft nacelle provided with at least 1 composite support;
FIG. 2 is a schematic view of the installation of the composite support inside the nacelle section;
FIG. 3 is a schematic view of the combination support; wherein fig. 3(a) is a schematic view of the component parts of the built-up stand, fig. 3(b) is a front view of the built-up stand, and fig. 3(c) is a top view of the built-up stand;
FIG. 4 is a schematic view of the connection of the wall plate and the column in the composite support;
FIG. 5 is a schematic view of the installation of the combination pedestal wall and column with other reinforcing members;
FIG. 6 is a schematic view of a panel construction; wherein FIG. 6(a) is a schematic of a panel inner side structure, FIG. 6(b) is a schematic of a panel outer side structure, and FIG. 6(c) is a panel top view;
FIG. 7 is a schematic view of a column configuration; wherein FIG. 7(a) is a top view of the column, FIGS. 7(b) and 7(c) are isometric views of the column, FIG. 7(D) is a cross-sectional view of columns D-D, and FIG. 7(E) is a cross-sectional view of columns E-E;
FIG. 8 is a detail view of the wall and column combination; wherein FIG. 8(a) is a front view of the assembly, FIG. 8(B) is a sectional view of the assembly B-B, FIG. 8(C) is a sectional view of the assembly A-A, and FIG. 8(d) is a sectional view of the assembly C-C;
FIG. 9 is a first angle bearing isometric view;
FIG. 10 is a second gusset isometric view;
FIG. 11 is an isometric view of a third temple;
FIG. 12 is a fourth angle bracket isometric view;
FIG. 13 is a first sprag isometric view;
FIG. 14 is a second sprag isometric view;
FIG. 15 is a schematic illustration of a stiffener plate configuration, wherein FIGS. 15(a), 15(b) are isometric views of the stiffener plate, and FIG. 15(c) is a three-view of the stiffener plate;
FIG. 16 is a schematic view of the aircraft or spacecraft nacelle pendulum assembly shaft, crank and drive assembly installation;
fig. 17 shows an example of the use of a cabin.
In the figure, 1-semi-hard shell cabin section, 2-combined support, 3-wall plate, 4-column body, 5-first angle brace, 6-second angle brace, 7-third angle brace, 8-fourth angle brace, 9-first inclined brace, 10-second inclined brace, 11-reinforcing plate, 12-screw, 13-nut and washer, 14-installation space, 15-rotating shaft, 16-crank, 17-driving device;
101-upper reinforcing frame, 102-lower reinforcing frame, 103-reinforced joint;
301-groove-shaped gap, 302-circular through hole, 303-flange mounting surface, 304-bolt hole, 305-threaded hole, 306-nut mounting groove, 307-boss, 308-pin hole, 309-radial reinforcing rib, 3011-horizontal reinforcing rib, 3012-outer side bearing mounting step;
401-flange, 402-gap, 403-threaded hole, 404-threaded hole, 405-weight reduction groove, 406-small plane, 407-inner side bearing mounting step, 408-crank positioning step;
501-horizontal flanging, 502-vertical flanging, 503-reinforcing rib;
601-horizontal flanging, 602-vertical flanging, 603-reinforcing rib;
701-horizontal flanging, 702-vertical flanging, 703-reinforcing rib;
801-horizontal flanging, 802-vertical flanging, 803-reinforcing rib;
901-L-shaped joint, 902-circular arc joint, 903-connecting beam;
1001-L-shaped joint, 1002-arc-shaped joint, 1003-connecting beam;
1101, cylindrical surface flange, 1102, plane flange, 1103, notch, 1104 and floating nut.
D1、D2、D3、D4The inner diameter of a cylindrical cavity of the combined support;
δ1-outer ring thickness of the outer bearing;
δ2-the thickness of the outer ring of the inner bearing;
d0-column diameter;
c1-distance between the middle surface of the column peripheral gap and the transverse rib of the wall plate;
c2-the distance between the middle surface of the column circumferential notch and the end surface of the column;
l1-distance between column axis and wall left axis;
l2-distance between column axis and boss pin hole axis;
h1-distance between the axis of the column and the lower end of the wall plate;
h2-distance between the axis of the column and the upper end of the wall plate;
alpha is the included angle between the first inclined strut and the axis of the column body;
beta is the included angle between the second inclined strut and the axis of the column body;
gamma-stiffener tilt angle;
L0length of the drive device below zero.
Detailed Description
For a better understanding of the present invention, reference is made to the following detailed description taken in conjunction with the accompanying drawings.
As shown in fig. 1, the cabin of the aircraft or spacecraft of the invention is composed of a semi-hard shell cabin section 1 and at least 1 combined support 2, and fig. 1 shows the case that the cabin has 2 combined supports 2.
As shown in fig. 2, the combined support 2 is installed inside the cabin 1, an upper reinforcing frame 101 is arranged above the combined support 2, and a lower reinforcing frame 102 and a joint reinforcing head 103 are arranged below the combined support 2; the reinforcing rib 104 at the inner side of the cabin section 1 is embedded into the groove-shaped notch 301 of the combined support 2.
As shown in fig. 3(a) and 3(b), the combined support structure is shown, the combined support 2 includes a wall plate 3, a column 4, a first corner brace 5, a second corner brace 6, a third corner brace 7, a fourth corner brace 8, a first inclined brace 9, a second inclined brace 10, a reinforcing plate 11, and the like, the wall plate 3 and the column 4 form a main structure of the combined support 2, and the main structure is reinforced by the first corner brace 5, the second corner brace 6, the third corner brace 7, the fourth corner brace 8, the first inclined brace 9, the second inclined brace 10, the reinforcing plate 11, and the like. As shown in fig. 3(c), the wall plate 3, the column 4 and the reinforcing plate 11 form a sufficient installation space 14 for installing a driving device 17 for driving the swinging member to swing.
As shown in fig. 4, a connection between the wall plate 3 and the column 4 is shown, and the column 4 is tightly connected with the wall plate 3 through a screw 12 and a nut and washer 13, and a screw 12 and a threaded hole 305 on the wall plate 3;
as shown in fig. 5, the connection relationship among the components inside the combined support 2 is given, the upper surface of the wall plate 3 is connected with the upper reinforcing frame 101 of the cabin section 1, the lower surface of the wall plate is connected with the lower reinforcing frame 102 of the cabin section 1, and one side of the wall plate 3, which is tightly attached to the cabin section 1, is provided with a groove-shaped notch 301 which is connected with the reinforcing rib 104 of the cabin section 1; the wall plate 3 provides an interface for a driving device 17; the cylinder 4 is hollow, and a bearing and a swinging part rotating shaft 15 are arranged; the first corner brace 5, the second corner brace 6, the third corner brace 7 and the fourth corner brace 8 are respectively positioned at four corners of the wall plate 3, one side of each corner brace is connected with the side surface of the wall plate 3, and the other side of each corner brace is connected with the reinforcing frames 101 and 102; the first inclined strut 9 and the second inclined strut 10 are both of a spatial structure, one end of each first inclined strut is connected with the inner corner of the wall plate 3, and the other end of each first inclined strut is connected with the side face of the column 4; one end of the reinforcing plate 11 is connected with the inner side of the wall plate 3, and the other end is connected with the column 4.
As shown in fig. 6, a schematic view of the panel construction is given. Fig. 6(a) shows a schematic view of the inner surface of the wall plate 3, and it can be seen that the wall plate 3 is provided with a circular through hole 302 for the rotating shaft 15 to pass through and mount, the circular through hole 302 is matched with the cavity of the column body 4, a flange mounting surface 303 is arranged by taking the circular through hole 302 as the center, bolt holes 304 are axially and uniformly distributed, a threaded hole (305) is arranged in the solid area below the circular through hole (302), the bolt hole (304) and the threaded hole (305) are used for connecting with the column body (4), and a nut mounting groove (306) is arranged at the position of the outer surface of the wall; a boss 307 is arranged on the inner surface of the tail seat, which is far away from the circular through hole 302 and at the same horizontal height, and a pin hole 308 is dug in the boss 307 and is used for connecting with the tail seat of the driving device 17; with the circular through hole 302 as the center, a reinforcing rib is arranged, the radial reinforcing ribs 309 point to four corners of the wall plate 3, wherein a horizontal reinforcing rib 3011 is arranged between the circular through hole 302 and the pin hole 308. Fig. 6(b) shows a schematic view of the outer surface of wall plate 3, fig. 6(c) shows a top view of the wall plate, and the outer surface of wall plate 3 is provided with a groove-shaped notch 301, and the groove-shaped notch 301 is matched with the corresponding reinforcing rib 104 of cabin section 1, and can penetrate through the wall plate structure or not.
As shown in fig. 7, a schematic diagram of a column structure is given, and it can be known that the column is a hollow cylindrical structure with a flange 401, wherein the flange 401 is matched with a flange on a wall plate; a notch 402 along the circumferential direction is formed on the cylinder body close to the flange 401, so that the crank 16 in the part of the rotating shaft 15 is allowed to extend out and a certain swinging space is provided, and the extending end of the crank 16 is connected with the driving device 17; the end face of the cylinder 4 is provided with a threaded hole 403 for connecting with a bearing end cover of the rotating shaft 15, and the outer surface of the end face of the cylinder 4 is provided with a threaded hole 404 for connecting with the first inclined strut 9, the second inclined strut 10 and the reinforcing plate 11; the outer surface of the cylinder 4 is provided with weight-reducing grooves 405 which are distributed circumferentially; the lower end of the post 4 is formed with a facet 406 flush with the lower surface of the wall 3.
As shown in fig. 8, a detailed view of the wall plate and column body assembly is shown, and as shown in fig. 8(a) and 8(b), the circular through hole 302 and the hollow cavity of the column body 4 together form a serial cylindrical cavity, wherein a bearing mounting step 3012 is provided at one end of the cavity close to the wall plate 3 for mounting a bearing outside the rotating shaft 15, and a bearing mounting step 407 and a crank positioning step 408 are provided at one end of the cavity close to the column body 4.
As shown in fig. 8(c) and 8(d), the critical dimension relations of the combined support are also given: by the circular through-hole 302 of wallboard 3 and the 4 cavity of cylinder, 15 installation interfaces of pivot have been constituted jointly, wherein the cavity is close to 3 one ends of wallboard and has bearing installation step 3012 to be used for installing 15 outside bearings of pivot, the cavity is close to 4 one ends of cylinder and has bearing installation step 407, be used for installing 15 bearings of pivot, form two face of cylinder diameter D1 of bearing installation step 3012, D2, and the straight D3 of two face of cylinders that form bearing installation step 407, D4, satisfy respectively:
(D1-D2)/2＜δ1
(D3-D4)/2＜δ2
wherein, delta 1 is the outer ring thickness of the bearing outside the rotating shaft (15), and delta 2 is the outer ring thickness of the bearing inside the rotating shaft (15).
In the combined support 2, the diameter D0 of the column 4, the distance C1 between the middle plane of the circumferential notch of the column 4 and the horizontal reinforcing rib 3011 of the wall plate 3, the distance C2 between the middle plane of the notch 402 of the column 4 and the end plane of the column 4, the distance L1 between the axis of the column 4 and the left edge of the wall plate 3, the distance L2 between the axis of the column 4 and the axis of the pin hole 308, the distance H1 between the axis of the column 4 and the lower end plane of the wall plate 3, the distance H2 between the axis of the column 4 and the upper end plane of the wall plate 3, the included angle α between the first inclined strut 9 and the axis of the column 4, the included angle β between the second inclined strut 10:
the offset angle δ of the notch 402 of the column 4 satisfies:
wherein L is0The length of the drive in the zero position.
As shown in fig. 9 to 12, the first corner brace 5, the second corner brace 6, the third corner brace 7 and the fourth corner brace 8 are sequentially shown in an axonometric view, each corner brace part is composed of horizontal flanges 501, 601, 701, 801 and vertical flanges 502, 602, 702, 802, reinforcing ribs 503, 603, 703, 803 are arranged between the flanges, the horizontal flanges 501, 601, 701, 801 are arched and are matched and connected with the reinforcing frames 101, 102 of the cabin section 1, and the vertical flanges 502, 602, 702, 802 are rectangular and are matched and connected with the side wall of the wall plate 3.
As shown in fig. 13 to 14, axonometric views of the first sprag 9 and the second sprag 10 are given in this order. The diagonal brace is of a space structure, one end of the diagonal brace is provided with L-shaped joints 901 and 1001, the other end of the diagonal brace is provided with arc-shaped joints 902 and 1002, and the two ends of the diagonal brace are connected into a whole through middle connecting beams 903 and 1003; the L-shaped joint 901 of the first inclined strut 9 is connected with the upper left corner of the wallboard 3, and the L-shaped joint 1001 of the second inclined strut 10 is connected with the lower left corner of the wallboard 3; the included angles alpha and beta between the first inclined strut 9 and the second inclined strut 10 and the axis of the column 4 are all in the range of 30-45 degrees.
As shown in fig. 15, a schematic structural diagram of the reinforcing plate 11 is shown, one end of the reinforcing plate is a cylindrical flange 1101 and is connected with the cylinder 4, see fig. 15(a) in detail, one end of the reinforcing plate is a planar flange 1102 with a notch 1103, a floating nut 1104 is mounted on the inner side of the planar flange 1102, see fig. 15(c) in detail, the planar flange 1102 is mounted on the inner side of the right wall of the wall plate 3, and the reinforcing plate 11 and the wall plate 3 are connected together through a screw which penetrates through the outer side.
As shown in fig. 16, when the present invention performs a normal function, the swing member rotating shaft 15 is installed in the cavity of the combined support 2, the driving device 17 is installed in the installation space, the driving device 17 is a cylinder type linear driving device, one end of the driving device 17 is connected with the crank 16 part on the rotating shaft 15, and the other end is connected with the boss 307 pin hole 308 on the wall plate 3.
As shown in fig. 17, an application example is given when the swing component outside the cabin in the atmosphere is a grid rudder, in the example, when the grid rudder swings, the boss 307 structure of the combined support 2 provides a support reaction force for the power source, and the grid rudder is guaranteed to swing normally. When the grid rudder is subjected to a great acting force due to air flow scouring, a concentrated force and a large bending moment are generated at the root parts of the cabin section 1 and the rotating shaft 15, the concentrated force can be transmitted to the reinforcing frames 101 and 102, the reinforcing ribs 104 and the reinforcing joints 103 of the cabin section 1 through the radiation type reinforcing members (such as the first inclined strut 9 and the second inclined strut 10) and the reinforcing ribs 309 and 3011 on the wall plate 3, and in the transmission process, the concentrated force is converted into a uniform force load or a small concentrated force load which can be borne by the cabin section 1, so that an aircraft or spacecraft cabin can bear the large concentrated force load brought by the grid rudder.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Claims (9)
1. An aircraft cabin structure characterized in that: comprises a cabin section (1) and at least one combined support (2); the cabin section (1) is a semi-hard shell with a transverse upper reinforcing frame (101), a transverse lower reinforcing frame (102) and a vertical reinforcing rib (104); the combined support (2) is positioned at the inner side of the cabin section (1), and a reinforced joint (103) is arranged below the combined support (2);
combination support (2) contain wallboard (3), cylinder (4), bracing (5, 6, 7, 8), first bracing (9), second bracing (10), reinforcing plate (11), and wallboard (3) and cylinder (4) constitute the major structure of combination support (2), strengthen through each bracing (5, 6, 7, 8), first bracing (9), second bracing (10), reinforcing plate (11), wherein:
the upper surface of the wall plate (3) is connected with an upper reinforcing frame (101) of the cabin section (1), the lower surface of the wall plate is connected with a lower reinforcing frame (102) of the cabin section (1), and one side of the wall plate (3) clinging to the cabin section (1) is provided with a groove-shaped notch (301) which is connected with a reinforcing rib (104); the wall plate (3) provides an interface of a driving device (17);
the column body (4) is tightly connected with the wall plate through a screw (12), a nut and a gasket (13) and a screw (12) and a threaded hole (305) on the wall plate (3); the cylinder (4) is hollow and is provided with a bearing and a rotating shaft (15) of a swinging component;
the angle braces (5, 6, 7, 8) are positioned at four corners of the wall plate (3), the vertical flanging in each angle brace part is connected with the side surface of the wall plate (3), and the horizontal flanging in each angle brace part is connected with the upper reinforcing frame (101) and the lower reinforcing frame (102);
one end of the first inclined strut (9) and one end of the second inclined strut (10) are connected with the inner corner of the wall plate (3), and the other ends of the first inclined strut and the second inclined strut are connected with the side surface of the column body (4);
one end of the reinforcing plate (11) is connected with the inner side of the wall plate (3), and the other end is connected with the column body (4);
the combined support (2) is provided with an installation space (14) formed by a wall plate (3), a column body (4) and a reinforcing plate (11) and used for installing a driving device (17) for driving the swinging component to swing.
2. The aircraft cabin structure of claim 1, wherein: the outer surface of the wall plate (3) is provided with a groove-shaped notch (301), the groove-shaped notch (301) is matched with the corresponding reinforcing rib (104), and the groove-shaped notch (301) penetrates through or does not penetrate through the wall plate structure;
the wall plate (3) is provided with a circular through hole (302) for the rotating shaft (15) to pass through, the circular through hole is matched with the cavity of the cylinder (4), a flange mounting surface (303) is arranged by taking the circular through hole (302) as the center, bolt holes (304) are axially and uniformly distributed, a threaded hole (305) is formed in a solid area below the circular through hole (302), the bolt holes (304) and the threaded hole (305) are used for being connected with the cylinder (4), and a nut mounting groove (306) is formed in the outer surface of the wall plate corresponding to the bolt holes (304); a boss (307) is arranged on the inner surface far away from the circular through hole (302) and at the same horizontal height, and a pin hole (308) is dug in the boss (307) and used for being connected with a tailstock of the driving device (17);
reinforcing ribs are arranged by taking the circular through hole (302) as the center of a circle, the radial reinforcing ribs (309) point to the four corners of the wall plate (3), and horizontal reinforcing ribs (3011) are arranged between the circular through hole (302) and the pin holes (308); an outer bearing mounting step (3012) is provided on the outward side of the circular through hole (302).
3. An aircraft cabin structure according to claim 2, characterized in that: the column body (4) is of a hollow cylindrical structure with a flange (401), wherein the flange (401) is matched with a flange on a wall plate; a notch (402) along the circumferential direction is formed on the cylinder body close to the flange (401) to allow a crank (16) in the rotating shaft (15) part to extend out and provide a certain swinging space, and the extending end of the crank (16) is connected with a driving device (17); the end face of the cylinder (4) is provided with a threaded hole (403) for connecting with a bearing end cover of the rotating shaft (15), and the outer surface of the end face of the cylinder (4) is provided with a threaded hole (404) for connecting with the first inclined support (9), the second inclined support (10) and the reinforcing plate (11); the outer surface of the cylinder (4) is provided with weight-reducing grooves (405) which are distributed circumferentially; the inner part of the hollow cavity of the cylinder (4) is provided with an inner side bearing mounting step (407) and a crank positioning step (408); the lower end of the column body (4) is provided with a small plane (406) which is flush with the lower surface of the wall plate (3).
4. An aircraft cabin structure according to claim 3, characterized in that: circular through-hole (302) and cylinder (4) cavity have constituted the cylindrical cavity of series connection jointly for hold pivot (15), wherein the cavity is close to wallboard (3) one end and has outside bearing installation step (3012) and be used for installing pivot (15) outside bearing, the cavity is close to cylinder (4) one end and has inside bearing installation step (407), be used for installing pivot (15) inside bearing, form two face of cylinder diameters D1, D2 of outside bearing installation step (3012), and form two face of cylinder diameters D3, D4 of inside bearing installation step (407).
5. The aircraft cabin structure of claim 1, wherein: each corner support is composed of a horizontal flanging and a vertical flanging, a reinforcing rib is arranged between the flanging, the horizontal flanging is matched and connected with an upper reinforcing frame (101) and a lower reinforcing frame (102) of the cabin section (1) in an arched manner, and the vertical flanging is matched and connected with the side wall of the wall plate (3) in a rectangular manner.
6. The aircraft cabin structure of claim 1, wherein: the first inclined strut (9) and the second inclined strut (10) are of a space structure, one end of each first inclined strut is an L-shaped joint, the other end of each first inclined strut is an arc-shaped joint, and the two ends of each first inclined strut and the two ends of each second inclined strut are connected into a whole through a middle connecting beam; a first L-shaped joint (901) of the first inclined strut (9) is connected with the upper left corner of the wallboard (3), and a second L-shaped joint (1001) of the second inclined strut (10) is connected with the lower left corner of the wallboard (3); the included angles alpha and beta between the first inclined strut (9) and the axis of the second inclined strut (10) and the axis of the column body (4) are all in the range of 30-45 degrees.
7. The aircraft cabin structure of claim 1, wherein: reinforcing plate (11) one end is cylinder turn-ups (1101), is connected with cylinder (4), and one end is plane turn-ups (1102) of taking breach (1103), and the inboard nut that moves about of installing of plane turn-ups (1102) is installed in wallboard (3) right side inboard, links together reinforcing plate (11) and wallboard (3) through the screw that the outside penetrated.
8. The aircraft cabin structure of claim 1, wherein: the cabin section (1) and the combined support (2) are made of metal or fiber composite materials or combination of metal and fiber composite materials.
9. The aircraft cabin structure of claim 1, wherein: the connection mode among the wallboard (3), the column body (4), the angle braces (5, 6, 7, 8), the first inclined brace (9), the second inclined brace (10) and the reinforcing plate (11) adopts screw connection or rivet connection or glue solution bonding.
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| CN201910441174.4A CN110466801B (en) | 2019-05-24 | 2019-05-24 | Aircraft cabin structure |
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| CN110466801B true CN110466801B (en) | 2021-03-02 |
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| CN111673152B (en) * | 2020-05-26 | 2021-07-30 | 上海航天精密机械研究所 | Manufacturing method of cabin body suitable for lunar exploration orbital vehicle |
| CN112572839A (en) * | 2020-12-08 | 2021-03-30 | 长光卫星技术有限公司 | Momentum wheel combined bracket for batch processing |
| CN114234836B (en) * | 2021-11-16 | 2023-12-19 | 北京卫星制造厂有限公司 | Method for assembling large complex sealed cabin structure of space station in part |
| CN114348306A (en) * | 2021-11-16 | 2022-04-15 | 北京卫星制造厂有限公司 | Underwater simulation training trolley for spacecraft cabin |
| CN114659415B (en) * | 2022-03-01 | 2024-02-09 | 航天科工火箭技术有限公司 | Light cabin section structure of carrier |
| CN116900423B (en) * | 2023-06-15 | 2024-02-13 | 北京新风航天装备有限公司 | Pneumatic tapping tool and method for screw hole fitter with outer circumference of cabin perpendicular to axis |
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| CN103759597A (en) * | 2014-01-14 | 2014-04-30 | 北京航空航天大学 | Missile cabin radial monoclinic bushing bolt connection structure |
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| US10011372B2 (en) * | 2015-10-29 | 2018-07-03 | The Boeing Company | Systems and methods for shielding structures from radiation and magnetic field exposure |
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