CN114212276A - Space station cabin door and method for assembling and adjusting cabin door sealing structure - Google Patents
Space station cabin door and method for assembling and adjusting cabin door sealing structure Download PDFInfo
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- CN114212276A CN114212276A CN202111440936.2A CN202111440936A CN114212276A CN 114212276 A CN114212276 A CN 114212276A CN 202111440936 A CN202111440936 A CN 202111440936A CN 114212276 A CN114212276 A CN 114212276A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/12—Artificial satellites; Systems of such satellites; Interplanetary vehicles manned
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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 a space station cabin door, which comprises a pressing component (1), wherein the pressing component is provided with a handle part and a pressing part, the pressing component is hinged to the upper part of a door frame component (2) at a position close to the pressing part and comprises a cabin door component (3), and the upper surface of the edge part of a sealing sleeve is in sealed tight contact with a sealing pressing block in a sealing way in a closed state of the space station cabin door; the lower surface of the edge portion is in close sealing contact with the upper surface of the lower portion of the door frame assembly. The sealing structure of the cabin door provided by the invention is simple and easy to operate, and the sealing operation of the multi-stage sealing structure can be completed at one time only by manually rotating the pressing assembly to the pressing position; the assembly difficulty in assembling the sealing structure can be obviously reduced by using the assembly and adjustment method provided by the invention, the assembly can be completed by adjusting the sealing element only by simple installation when a astronaut is in orbit, the assembly steps are simple, and the efficiency is high. The difficulty of assembly operation of astronauts can be reduced.
Description
Technical Field
The invention relates to the technical field of manned spaceflight, in particular to a space station cabin door and an assembling and adjusting method of a space station cabin door sealing structure.
Background
The split type cabin door is a sealed cabin door designed for emergency disposal capability of a space station, and the structural form of the split type cabin door is different from that of a conventional integral sealed cabin door. The door body of the split type cabin door of the space station is of a split type assembly structure, the space station needs to be sent in a part form, and the space station is assembled in the space station operated by astronauts in an orbit.
The traditional cabin doors are assembled on the ground, and the components can run in orbit without astronauts. The split type cabin door is launched in a state of parts and assembled by astronauts in orbit; the traditional cabin door body is of an integrated structure, the number of the compression points is large, the split type cabin door is of a door body assembly type structure, the number of the compression points is only half of the number of the compression points of the traditional cabin door, the number of the compression points is small, and the rigidity of the integral structure of the cabin door is weak. The split type cabin door comprises a multi-stage sealing structure, the sealing structure is different from the traditional sealing cabin door, and the split type cabin door meeting the sealing requirement can be finally assembled by installing and adjusting the sealing element. Because the constraints on the sealing structure are numerous and not intuitive. If the sealing element is installed and adjusted by the astronaut in orbit, higher requirements are necessarily put on the assembling operation of the astronaut, and doubts exist whether the sealing performance of the assembled cabin door meets the sealing requirements or not. Aiming at the characteristics of the split type cabin door of the space station, the installation and adjustment work of the sealing structure of the split type cabin door of the space station has the following problems:
because the split type cabin door of the space station is launched to the space in a part state, the split type cabin door needs to be assembled by astronauts in orbit, and the assembly operation difficulty of the astronauts is high; and the split type cabin door of the weak rigid space station under the multi-constraint condition has a multi-stage sealing structure, and the assembly and adjustment work steps of the multi-stage sealing structure are complex and the efficiency is low.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, and the space station cabin door and the assembling and adjusting method of the space station cabin door sealing structure are provided. The cabin door provided by the invention has a simple sealing structure and is easy to operate; the assembling and adjusting method provided by the invention can obviously reduce the assembling difficulty when the sealing structure is assembled, and has simple assembling steps and high efficiency. The difficulty of assembly operation of astronauts can be reduced.
In one aspect, the space station hatch according to the present invention comprises a pressing assembly having a handle portion and a pressing portion, the pressing assembly being hinged to an upper portion of a door frame assembly at a position adjacent to the pressing portion, comprising:
a door assembly, wherein the upper surface of the edge part is tightly contacted with the pressing part of the pressing assembly in a sealing way under the state that the space station door is closed; the lower surface of the edge portion is in close sealing contact with the upper surface of the lower portion of the door frame assembly.
The door frame assembly is fixedly installed on the cabin body of the space station and is an installation foundation of the cabin door of the space station. The compressing components are uniformly distributed and compress the edge part of the cabin door component to form a compressing point. The amount of compression force at the compression point is the maximum amount of compression force experienced by the overall door assembly. The edge part of the door assembly in the middle between every two adjacent compression points is a central point, and the value of the pressing force at the central point is the minimum value of the pressing force applied to the whole door assembly. When the pressing assembly is used, the pressing assembly is pulled to the pressing position, and the space station cabin door can be pressed and fixed on the space station cabin body in a medium sealing mode.
Further, the air conditioner is provided with a fan,
the door assembly includes:
the door body is characterized in that a boss is arranged on the upper surface of the edge part of the door body;
the sealing sleeve is wrapped on the upper surface, the side edge and the lower surface of the edge part of the door body, wherein an opening is formed in the sealing sleeve positioned on the upper surface of the door body; the boss is exposed from the opening; and
the sealing pressing block is fixedly arranged on the door body and is positioned at the upper part of the boss;
one surface of the sealing pressing block is a repairing plane, and a first annular bulge part and a second annular bulge part which are concentric and have the same height are arranged at two ends of the other surface opposite to the repairing plane; a groove is formed in the other side of the sealing pressing block at the circle center positions of the first protruding part and the second protruding part; the groove between the first boss and the second boss is a space for accommodating the boss, and the groove is positioned in the center of the sealing pressing block; the height of the groove is smaller than that of the boss; in a state that the cabin door of the spatial station is closed, the pressing part of the pressing assembly is in close contact with the repairing plane; the first protruding portion and the second protruding portion are in tight contact with a sealing sleeve on the periphery of the boss in a sealing mode, and the upper surface of the boss is in tight contact with the bottom surface of the groove.
The cross sections of the first bulge part and the second bulge part are arc-shaped and are annularly arranged on the other surface of the sealing pressing block. There is no associated positional relationship between the groove bottom surface of the groove and the other face of the sealing compact. The section of the sealing sleeve is U-shaped and is integrally formed. When the pressing assembly is in a pressing position and the door body is in sealing connection with the door frame assembly, the first protruding portion and the second protruding portion of the sealing pressing block are in medium sealing abutting contact with the sealing sleeves on the upper surface of the edge portion of the door body, and meanwhile the upper surface of the boss is in rigid tight contact with the bottom surface of the groove. And the sealing sleeve at the lower surface of the edge part of the door body is in medium-sealing abutting contact with the door frame assembly.
In another aspect, the method for assembling and adjusting a sealing structure of a hatch of a space station according to the present invention comprises the steps of:
s1, reserving process allowance in the height direction when the boss and the sealing pressing block are processed, processing the sealing pressing block tooling part, and reserving process allowance in the height direction;
s2, adopting a repairing method to repair the height of the boss to ensure that the seal between the seal pressing block and the seal sleeve meets the requirements of the seal compression amount and the leakage rate of the space station;
s3, after the door body assembly and the sealing sleeve are assembled, a sealing pressure block tooling piece is fixed to the door body, the compression amount of the sealing sleeve is adjusted by increasing or decreasing tooling gaskets by a repair method, the sum of the heights of the sealing pressure block tooling piece and the tooling gaskets, which can ensure that the sealing between the door body and the door frame meets the requirements of the sealing compression amount of a space station and the leakage rate, is obtained, and the height of a sealing pressure block is repaired according to the sum of the heights of the sealing pressure block tooling piece and the tooling gaskets;
and S4, replacing a sealing pressing block tooling piece and a tooling gasket with a sealing pressing block, completing assembly of the cabin door of the space station, sealing the door body assembly and the door frame assembly with the pressing assembly, measuring the sealing between the door body and the door frame to meet the requirements of the sealing compression amount and the leakage rate of the space station, and applying an operating force on the handle part of the pressing assembly to meet the requirements of the aerospace human engineering system.
Through the steps, the high-precision sealing pressing block can be obtained, and the sealing pressing block can meet the sealing requirement of the cabin door by being directly installed to the cabin door without being adjusted or processed by a astronaut in orbit.
Further, the method for assembling and adjusting the sealing structure of the cabin door of the space station according to the present invention further comprises the steps of:
and S5, disassembling the cabin door of the space station, recording the accurate height of the sealing pressing block, and making a pair mark with the corresponding boss.
The sealing pressing block meeting the sealing requirement and the leakage rate requirement through testing is marked with the boss on the door body on the ground, so that the sealing pressing block cannot be mistakenly arranged when the astronaut installs on the rail, and the leakage accident cannot be caused.
Further, the method for adjusting the sealing structure of the hatch of the spatial station according to the present invention, in the step S2, comprises the steps of:
s21, calculating the theoretical value of the boss height by using a sealing compression ratio formula;
s22, repairing the process allowance of the boss height according to the boss height theoretical value;
and S23, after the repair is finished, measuring and recording the actual height of the boss, and performing sealing compression ratio recalculation according to the actual height of the boss to ensure that the design index is met.
The height of the boss after being repaired can meet the requirement that when the compression assembly is located at the compression position, the upper surface of the boss is in rigid close contact with the bottom surface of the groove, and meanwhile, the first protruding portion and the second protruding portion of the sealing pressing block compress the sealing sleeve around the boss by a certain compression amount. The value of a certain compression amount of the seal sleeve compressed at the periphery of the boss is smaller than the thickness value b at the periphery of the opening of the seal sleeve. At this time, a contact surface formed by rigidly and closely contacting the upper surface of the boss with the groove bottom surface of the groove and the other surface of the sealing pressing block have no correlative position relation. That is, in the concept of the present invention, the heights of the first and second protrusions and the depth of the groove are independent of each other and can be controlled separately.
Further, according to the installation and adjustment method of the sealing structure of the hatch of the spatial station of the present invention,
in step S21, first, the height values c of the first and second protrusions of the seal compact and the thickness value b at the periphery of the seal gland opening are actually measured, and then the theoretical boss height value a is obtained from the calculation formula δ of the seal compression ratio, i.e., (b- (a-c))/b, according to the design index δ of the seal compression ratio between the seal compact and the seal gland.
Further, according to the installation and adjustment method of the sealing structure of the hatch of the spatial station of the present invention,
in step S3, the trimming plane is trimmed when the sealing compact is trimmed.
Further, according to the installation and adjustment method of the sealing structure of the hatch of the spatial station of the present invention,
in the step S3, the method includes the steps of:
s31, packing gaskets between the sealing press block tooling piece and the compression assembly, compressing the door body assembly and the door frame assembly through the compression assembly when one gasket is added after one gasket is packed, and then measuring and calculating the compression rate of a compression point, the compression rate of a central point and the operating force of the compression assembly in sequence until the compression rate of the sealing sleeve meets the sealing design requirement by the height sum of the sealing press block tooling piece and the added gaskets under the compression state, and performing quick leak detection to ensure that the leak rate meets the design requirement; wherein the content of the first and second substances,
the pressing points are contact points of the sealing pressing block and the door body, and the central point is positioned on the symmetrical center line of two adjacent pressing points and at the position of the door body and the door frame assembly;
and S32, in a compression state, the sum of the heights of the sealing press block tool piece and the added gasket is the required actual height of the sealing press block, and the sealing press block is repaired according to the actual height.
Further, according to the installation and adjustment method of the sealing structure of the hatch of the spatial station of the present invention,
in the step S31, the compression ratio of the compression point and the compression ratio of the center point are calculated by sequentially measuring the compression point and the seal gap d at the position corresponding to the center point when the compression assembly is in the compression state, and obtaining the compression ratio of the compression point and the compression ratio of the center point according to a calculation formula δ ═ h-d/d by combining the seal height h of the seal sleeve.
Further, according to the installation and adjustment method of the sealing structure of the hatch of the spatial station of the present invention,
in the step S4, the compression ratio of the compression point, the compression ratio of the center point, and the operation force of the compression assembly are measured and calculated by sequentially measuring the compression point and the seal gap d at the position corresponding to the center point while the compression assembly is in a compressed state, and calculating the compression ratio of the compression point and the compression ratio of the center point according to a formula δ ═ h-d/d by combining the seal height h of the seal sleeve and the seal compression ratio; and the sealing press block enables the compression ratio of the sealing sleeve to meet the sealing design requirement in a compression state, and the rapid leakage detection is carried out to ensure that the leakage rate meets the design requirement.
In step S4, the pressing member operating force is measured by using a push-pull force meter perpendicular to the end of the pressing member handle to measure the pressing and unlocking operating forces, respectively.
Compared with the prior art, the invention has the following remarkable beneficial effects: the sealing structure of the cabin door provided by the invention is simple and easy to operate, and the sealing operation of the multi-stage sealing structure can be completed at one time only by manually rotating the pressing assembly to the pressing position; the assembly difficulty in assembling the sealing structure can be obviously reduced by using the assembly and adjustment method provided by the invention, the assembly can be completed by adjusting the sealing element only by simple installation when a astronaut is in orbit, the assembly steps are simple, and the efficiency is high. The difficulty of assembly operation of astronauts can be reduced.
Drawings
Fig. 1 is a flowchart of an installation and adjustment method of a spatial station hatch seal structure according to an embodiment of the present invention;
FIG. 2 is a partial cross-sectional view of a spatial station bay door of one embodiment of the present invention;
FIG. 3 is a partial cross-sectional view of a door assembly of a space station door according to an embodiment of the present invention;
FIG. 4 is a schematic structural view of a space station bay door of one embodiment of the present invention;
fig. 5 is a schematic structural view of a space station door according to an embodiment of the present invention.
The reference numbers: 1-a compression assembly; 11-a handle portion; 12-a compacting section; 2-a door frame assembly; 3-a door assembly; 31-a door body; 31 a-boss; 32-sealing sleeve; 33-sealing and pressing the block; 33 a-a trim plane;
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
The present invention is described in detail below with reference to the drawings and the specific embodiments, which are not repeated herein, but the embodiments of the present invention are not limited to the following embodiments.
It should be noted that the structural features of the sealing press tooling member related to the present invention are the same as those of the sealing press 33, and the height dimension of the sealing press tooling member is smaller than the design height dimension of the sealing press 33. In the method for assembling and adjusting the sealing structure of the cabin door of the space station, for the purpose of assembling and adjusting, a sealing press block tooling piece is firstly used for replacing a sealing press block 33 to be installed on the door body, and in the subsequent step, the sealing press block tooling piece is replaced by the sealing press block 33.
As shown in fig. 2, 3, 4 and 5, the space station door according to one embodiment of the present invention includes a pressing assembly 1, the pressing assembly 1 having a handle part 11 and a pressing part 12, the pressing assembly 1 being hinged to an upper part of a door frame assembly 2 at a position adjacent to the pressing part 12, including:
a hatch door assembly 3 in which the trim plane 33a is in tight contact with the compression part 12 of the compression assembly 1 in a sealing manner in a state where the hatch door of the space station is closed; the lower surface of the edge portion is in close sealing contact with the upper surface of the lower portion of the door frame assembly 2.
Further, the door assembly 3 includes: a door 31, wherein the door 31 is provided with a boss 31a on the upper surface of the edge of the door 31; the sealing sleeve 32 covers the upper surface and the side edge of the door body 31 and the lower surface of the edge part of the door body, and an opening is formed in the sealing sleeve 32 positioned on the upper surface of the edge part of the door body 31; the boss 31a is exposed from the opening; a sealing press block 33 fixedly mounted on the door body 31 and positioned above the boss 31 a; one surface of the sealing pressing block 33 is a trimming plane 33a, and a first annular bulge part and a second annular bulge part which are concentric circles and have the same height are arranged at two ends of the other surface opposite to the trimming plane 33 a; a groove is formed in the other side of the sealing pressing block at the circle center positions of the first protruding part and the second protruding part; the groove between the first boss and the second boss is a space for accommodating the boss 31a, and the groove is located at the center of the sealing pressing block 33; the height of the groove is less than that of the boss 31 a; in a state where the cabin door of the spatial station is closed, the pressing part 12 of the pressing assembly 1 is in close contact with the trim plane 33 a; the first and second protrusions are in tight contact with the sealing sleeve 32 around the boss 31a in a sealing manner, and the upper surface of the boss 31a is in tight contact with the bottom surface of the groove. The first and second protrusions have circular arc-shaped cross sections and are annularly disposed on the other surface of the sealing press 33. There is no associated positional relationship between the groove bottom surface of the groove and the other face of the sealing compact 33.
Specifically, the door frame assembly 2 is circular and is fixedly mounted on the cabin. The hatch door assembly 3 comprises a door body 31 and 3 sealing pressing blocks 33. The door body 31 is composed of two semicircular door bodies 31, 3 bosses 31a are uniformly arranged on the edge part of the door body 31, and 3 sealing press blocks 33 are fixedly arranged on the door body 31 at the positions matched with the 3 bosses 31 a. On the door frame assembly 2, 3 pressing assemblies 1 are hinged at the positions matched with the 3 bosses 31 a. The sealing member covers the upper, side and lower surfaces of the edge portion of the door body 31.
In one embodiment of the present invention, as shown in fig. 1, a method of installing a door seal structure of a space station includes the steps of:
s1, reserving process allowance in the height direction when the boss 31a and the sealing press block 33 are machined, machining the sealing press block tooling part, and reserving process allowance in the height direction;
further, the method for assembling and adjusting the sealing structure of the cabin door of the space station according to the present invention further comprises the steps of:
s2, the height of the boss 31a is repaired by a repairing method, and the sealing between the sealing pressing block 33 and the sealing sleeve 32 is guaranteed to meet the requirements of the sealing compression amount and the leakage rate of the space station.
In particular, according to the installation and adjustment method of the sealing structure of the hatch of the space station of the present invention,
in step S2, the method includes the steps of:
s21, calculating the theoretical height value of the boss 31a by using a sealing compression ratio formula;
in step S21, first, the height values c of the first and second protrusions of the seal compact 33 and the thickness value b at the periphery of the opening of the seal sleeve 32 are actually measured, and then the index δ is designed according to the seal compression ratio between the seal compact 33 and the seal sleeve 32, and the theoretical height value a of the boss 31a is obtained from the calculation formula δ of the seal compression ratio ═ b- (a-c))/b.
S22, repairing the process allowance of the height of the boss 31a according to the theoretical value of the height of the boss 31 a;
and S23, after the repair is finished, measuring and recording the actual height of the boss 31a, and performing sealing compression ratio recalculation according to the actual height of the boss 31a to ensure that the design index is met.
The height of the modified boss 31a is satisfied that, when the compressing assembly 1 is in the compressing position, the upper surface of the boss 31a is in rigid close contact with the bottom surface of the groove, and the first and second protrusions of the sealing pressing block 33 compress the sealing sleeve around the boss 31a by a certain compression amount, wherein the value of the compression amount by which the sealing sleeve around the boss 31a is compressed is smaller than the thickness value b at the opening periphery of the sealing sleeve. At this time, the contact surface formed by the rigid close contact between the upper surface of the boss 31a and the groove bottom surface of the groove and the connection surface of the boss 31a and the seal pressing piece 33 are not in a correlated positional relationship with each other.
Further, the method for assembling and adjusting the sealing structure of the cabin door of the space station according to the present invention further comprises the steps of:
s3, after the assembly of the door body 31 assembly and the sealing sleeve 32 is completed, the sealing press block tooling piece is fixed to the door body 31, the compression amount of the sealing sleeve 32 is adjusted by increasing or decreasing the tooling gaskets by adopting a repairing method, the sum of the heights of the sealing press block tooling piece and the tooling gasket which can ensure that the sealing between the door body 31 and the door frame meets the sealing compression amount requirement and the leakage rate requirement of the space station is obtained, and the height of the sealing press block 33 is repaired according to the sum of the heights of the sealing press block tooling piece and the tooling gasket.
Specifically, in step S3, when the sealing compact 33 is fitted, the fitting plane 33a is fitted.
In step S3, the method includes the steps of:
s31, packing gaskets between the sealing press block tooling piece and the compression assembly 1, compressing the door body 31 assembly and the door frame assembly 2 through the compression assembly 1 after adding one gasket each time, measuring and calculating the compression rate of a compression point, the compression rate of a central point and the operating force of the compression assembly 1 in sequence until the sum of the heights of the sealing press block tooling piece and the added gaskets enables the compression rate of the sealing sleeve 32 to meet the sealing design requirement in a compression state, and performing quick leak detection to ensure that the leak rate meets the design requirement, wherein,
the pressing points are the contact points of the sealing pressing block 33 and the door body 31, and the central point is located at the position of the door body 31 and the door frame assembly 2 on the symmetrical center line of the two adjacent pressing points.
In step S31, the compression ratio of the compression point and the compression ratio of the center point are calculated by sequentially measuring the compression point and the seal gap d at the position corresponding to the center point when the compression assembly 1 is in the compression state, and obtaining the compression ratio of the compression point and the compression ratio of the center point according to the calculation formula δ ═ h-d/d of the seal compression ratio in combination with the height h of the seal ring of the seal gland 32.
And S32, in a compression state, the sum of the height of the sealing press block tooling and the added gasket is the required actual height of the sealing press block 33, and the sealing press block 33 is repaired according to the actual height.
Further, the method for assembling and adjusting the sealing structure of the cabin door of the space station according to the present invention further comprises the steps of:
s4, replacing a sealing pressing block tooling piece and a tooling gasket with a sealing pressing block 33, completing assembly of the cabin door of the space station, sealing the door body 31 assembly and the door frame assembly 2 by the pressing assembly 1, measuring that the sealing between the door body 31 and the door frame meets the requirement of the sealing compression amount and the leakage rate of the space station, and meeting the requirement of the aerospace human engineering system by the operating force applied to the handle part 11 of the pressing assembly 1.
Specifically, in step S4, the compression ratio of the compression point, the compression ratio of the center point, and the operating force of the compression assembly 1 are measured and calculated by sequentially measuring the compression point and the seal gap d at the position corresponding to the center point while the compression assembly 1 is in the compression state, and obtaining the compression ratio of the compression point and the compression ratio of the center point according to the calculation formula δ ═ h-d/d by combining the seal height h of the seal sleeve 32 and the seal compression ratio calculation formula δ ═ h-d/d; the sealing pressing block 33 enables the compression rate of the sealing sleeve 32 to meet the sealing design requirement in a pressing state, and the leakage rate is ensured to meet the design requirement by performing quick leakage detection.
In step S4, the operation force of the pressing member 1 is measured by using a push-pull force gauge perpendicular to the end of the handle of the pressing member 1 to measure the pressing and unlocking operation forces, respectively.
Further, the method for assembling and adjusting the sealing structure of the cabin door of the space station according to the present invention further comprises the steps of:
s5, disassembling the cabin door of the space station, recording the accurate height of the sealing pressing block 33, and making a pair mark with the corresponding boss 31 a.
In an embodiment of the present invention, as shown in fig. 3, first, a sufficient height process margin of 3 bosses 31a is reserved in a part processing stage of 2 semicircular door bodies 31; enough height process allowance is reserved in the machining stages of 3 sealing pressing blocks 33. And 3 sealing press block tooling parts are designed and processed simultaneously, the structural characteristics are the same as those of the 3 sealing press blocks 33, and the height dimension of the 3 sealing press block tooling parts is smaller than the design height of the 3 sealing press blocks 33.
For the sealing structure between the sealing compact 33 and the sealing sleeve 32 shown in fig. 3, the sealing between the sealing compact 33 and the sealing sleeve 32 is realized by controlling the height of the boss 31a of the door body 31. According to the sealing compression ratio calculation formula δ ═ b- (a-c))/b, the theoretical height value a of the boss 31a of the door body 31 ═ 1- δ b + c is calculated by actually measuring the heights c of the first boss and the second boss of the sealing pressure block 33 and the thickness value b of the sealing sleeve 32 and combining the sealing compression ratio design value δ. And (3) milling and repairing the height process allowance of the boss 31a of the door body 31 according to the theoretical height value a of the boss 31a of the door body 31, and strictly controlling the processing precision. The height of the boss 31a of the repaired door body 31 is measured, a sealing compression ratio calculation formula delta is substituted into (b- (a-c))/b, actual sealing compression ratio values of the sealing structure between the sealing pressing block 33 and the sealing sleeve 32 are respectively calculated, and the requirement of the sealing compression ratio design index of the structure is judged to be met.
Assembling the sealing cabin door, after assembling 2 semicircular door bodies 31 and the sealing sleeve 32 in place, assembling the sealing press block tooling parts of 3 sealing press blocks 33, and assembling 3 pressing components 1.
As shown in fig. 2, the overall sealing structure of the door body 31 between the door assembly 3 and the door frame assembly 2 is a sealing structure between the sealing sleeve 32 and the door frame assembly 2, a tool gasket is added between the sealing press block tooling of 3 sealing press blocks 33 and 3 pressing assemblies 1, 3 pressing points are sequentially measured when the 3 pressing assemblies 1 are in a pressing state, a sealing gap d at a position corresponding to 3 central points is obtained, a sealing ring height h of the sealing sleeve 32 is combined, a formula delta (h-d)/d is calculated according to a sealing compression ratio to obtain 3 compression ratios of the pressing points and 3 compression ratios of the central points, a push-pull dynamometer is perpendicular to the tail end of the handle 11 of the 3 pressing assemblies 1, the pressing and unlocking operation forces are measured to judge whether all the pressing points meet design requirements, and the thickness of the tool gasket of the 3 pressing points is adjusted until the compression ratios of the 3 pressing points, the compression ratios of the 3 central points, and the compression ratios of the 3 central points are obtained, The operating force of the 3 pressing assemblies 1 meets the requirement of design indexes. And (4) carrying out quick leak detection under the state to confirm that the leak rate meets the design index, and respectively measuring and recording the total height numerical values of the sealing press block tooling part and the tooling gasket at the 3 positions at the moment. And respectively carrying out milling and repairing on 3 sealing pressing blocks 33 at the positions of 3 pressing points according to the total height numerical values of the 3 sealing pressing block tooling parts and the tooling gaskets, and strictly controlling the machining precision. 3 sealed briquetting frock pieces and tool shim are replaced to 3 sealed briquetting 33 after will processing, install on hatch door subassembly 3, retest 3 and compress tightly some compression ratios, 3 central point compression ratios, 3 and compress tightly 1 operating force of subassembly to quick leak hunting judges that each index all should satisfy the design requirement. And then, detecting the thermal vacuum performance of the cabin door of the space station, and detecting that the operating force, the normal temperature and the vacuum leakage rate all meet the design indexes.
And then, detecting the thermal vacuum performance of the cabin door of the space station, and detecting that the operating force, the normal temperature and the vacuum leakage rate all meet the design indexes.
Finally, the space station hatch is disassembled into parts, the precise height of 3 press blocks is recorded, and the 3 press blocks and the corresponding 3 bosses 31a are made into a pair mark. So that the astronaut can identify the correct installation positions of the 3 pressing blocks during in-orbit installation.
The cabin door sealing structure in one embodiment of the invention is simple and easy to operate, and the sealing operation of the multi-stage sealing structure can be completed at one time only by manually rotating the pressing component 1 to the pressing position; the assembling and adjusting method in one embodiment provided by the invention can obviously reduce the assembling difficulty during assembling the sealing structure, and does not need to send the tool gasket to a space station. When the astronaut is in orbit, the number and the thickness of the tool gaskets do not need to be adjusted in orbit, the assembly can be completed only by simple installation and adjustment without the sealing pressing block 33, and the assembly step is simple and high in efficiency. The difficulty of assembly operation of astronauts can be reduced.
The foregoing is merely exemplary of particular embodiments of the present invention and devices and structures not specifically described therein will be understood to be embodied in the form of conventional devices and methods known in the art.
The above is only one embodiment of the present invention, and is not intended to limit the present invention, and it is obvious to those skilled in the art that various modifications and variations can be made in the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A space station door comprising a compression assembly (1), said compression assembly (1) having a handle portion (11) and a compression portion (12), said compression assembly (1) being hinged to an upper portion of a door frame assembly (2) at a location adjacent to said compression portion (12), comprising:
a door assembly (3) in which an upper surface of the edge portion is in tight contact with a pressing portion (12) of the pressing assembly (1) in a sealing manner in a state where the door of the space station is closed; the lower surface of the edge part is in close contact with the upper surface of the lower part of the door frame component (2) in a sealing way.
2. The space station compartment door of claim 1,
the door assembly (3) comprises:
the door body (31), the upper surface of the edge of the door body (31) is provided with a boss (31 a);
the sealing sleeve (32) is coated on the upper surface, the side edge and the lower surface of the edge part of the door body (31), and an opening is formed in the sealing sleeve (32) positioned on the upper surface of the door body (31); the boss (31a) is exposed from the opening; and
a sealing pressing block (33) fixedly mounted on the door body (31) and positioned above the boss (31 a); one surface of the sealing pressing block (33) is a repair plane (33a), and a first annular bulge part and a second annular bulge part which are concentric and have the same height are arranged at two ends of the other surface opposite to the repair plane (33 a); a groove is formed in the other surface of the sealing pressing block at the circle center positions of the first protruding part and the second protruding part, the groove is a space for accommodating the boss (31a), and the groove is located in the center position of the sealing pressing block (33); the height of the groove is smaller than that of the boss (31 a); the pressing part (12) of the pressing assembly (1) is in close contact with the repair plane (33a) in a state that the space station cabin door is closed; the first and second bosses are in sealing close contact with a sealing sleeve (32) around the boss (31 a); the upper surface of the boss (31a) is in close contact with the bottom surface of the groove.
3. A method of assembling the door sealing structure of the spatial station according to claim 2, comprising the steps of:
s1, reserving process allowance in the height direction when the boss (31a) and the sealing press block (33) are machined, machining the sealing press block tooling part, and reserving process allowance in the height direction;
s2, repairing the height of the boss (31a) by adopting a repairing method to ensure that the seal between the seal pressing block (33) and the seal sleeve (32) meets the requirements of the seal compression amount and the leakage rate of the space station;
s3, after the assembly of the door body (31) assembly and the sealing sleeve (32) is completed, a sealing pressure block tooling piece is fixed to the door body (31), the compression amount of the sealing sleeve (32) is adjusted by increasing or decreasing tooling gaskets by adopting a repair method, the sum of the heights of the sealing pressure block tooling piece and the tooling gaskets, which can ensure that the sealing between the door body (31) and a door frame meets the requirements of the sealing compression amount of a space station and the leakage rate, is obtained, and the height of a sealing pressure block (33) is repaired according to the sum of the heights of the sealing pressure block tooling piece and the tooling gaskets;
s4, replacing a sealing pressing block tooling piece and a tooling gasket with a sealing pressing block (33), completing assembly of the cabin door of the space station, sealing the door body (31) assembly and the door frame assembly (2) by the pressing assembly (1), measuring the sealing between the door body (31) and the door frame to meet the requirements of the sealing compression amount and the leakage rate of the space station, and applying the operating force on the handle part (11) of the pressing assembly (1) to meet the requirements of the aerospace human engineering system.
4. An assembly method for assembling the space station hatch seal structure of claim 3, further comprising the steps of:
s5, disassembling the space station cabin door, recording the accurate height of the sealing pressing block (33), and making a pair mark with the corresponding boss (31 a).
5. The method for setting up a door sealing structure of a space station according to claim 3,
in the step S2, the method includes the steps of:
s21, calculating the theoretical height value of the boss (31a) by using a sealing compression ratio formula;
s22, repairing the process allowance of the height of the boss (31a) according to the theoretical value of the height of the boss (31 a);
and S23, after the repair is finished, measuring and recording the actual height of the boss (31a), and performing sealing compression ratio recalculation according to the actual height of the boss (31a) to ensure that the design index is met.
6. The method for setting up a door sealing structure of a space station according to claim 5,
in the step S21, first, the height values c of the first and second protrusions of the sealing compact (33) and the thickness value (b) at the periphery of the opening of the sealing sleeve (32) are actually measured, and then the theoretical height value (a) of the boss (31a) is obtained from the calculation formula δ of the sealing compression ratio, which is (b- (a-c))/b, according to the sealing compression ratio design index (δ) between the sealing compact (33) and the sealing sleeve (32).
7. The method for setting up a door sealing structure of a space station according to claim 3,
in step S3, the fitting plane (33a) is fitted when the sealing compact (33) is fitted.
8. The method of assembling a sealing hatch sealing structure according to claim 7,
in the step S3, the method includes the steps of:
s31, packing gaskets between the sealing pressing block tooling part and the pressing assembly (1), pressing the door body (31) assembly and the door frame assembly (2) through the pressing assembly (1) after one gasket is packed, sequentially measuring and calculating the compression rate of a pressing point, the compression rate of a central point and the operating force of the pressing assembly (1) until the compression rate of the sealing sleeve (32) meets the sealing design requirement by the height sum of the sealing pressing block tooling part and the added gaskets under the pressing state, and performing quick leak detection to ensure that the leak rate meets the design requirement, wherein,
the pressing points are contact points of the sealing pressing block (33) and the door body (31), and the central point is positioned on the symmetrical center line of two adjacent pressing points at the positions of the door body (31) and the door frame assembly (2);
s32, in the pressing state, the sum of the height of the sealing press block tool and the added gasket is the required actual height of the sealing press block (33), and the sealing press block (33) is repaired according to the actual height.
9. The method for setting up a door sealing structure of a space station according to claim 8,
in the step S31, the compression ratio of the compression point and the compression ratio of the center point are calculated by sequentially measuring the compression point and the seal gap (d) at the position corresponding to the center point when the compression assembly (1) is in a compressed state, and obtaining the compression ratio of the compression point and the compression ratio of the center point according to a seal compression ratio calculation formula δ ═ h-d/d by combining with the seal ring height (h) of the seal sleeve (32).
10. The assembling and adjusting method of the sealing structure of the cabin door of the space station, according to the claim 3, is characterized in that in the step S4, the compression rate of the compression point, the compression rate of the center point and the operation force of the compression assembly (1) are measured and calculated by sequentially measuring the compression point and the sealing gap (d) at the corresponding position of the center point when the compression assembly (1) is in the compression state, combining the height (h) of the sealing ring of the sealing sleeve (32), and obtaining the compression rate of the compression point and the compression rate of the center point according to the calculation formula delta-d/d of the compression rate of the sealing ring, wherein in the compression state, the compression block (33) makes the compression rate of the sealing sleeve (32) meet the sealing design requirement, and carries out quick leak detection to ensure that the leak rate meets the design requirement;
in the step S4, the operation force of the pressing assembly (1) is measured by using a push-pull dynamometer perpendicular to the end of the handle of the pressing assembly (1) to measure the pressing and unlocking operation forces, respectively.
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