CN114212276B - Space station cabin door and assembling and adjusting method of cabin door sealing structure - Google Patents
Space station cabin door and assembling and adjusting method of cabin door sealing structure Download PDFInfo
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- CN114212276B CN114212276B CN202111440936.2A CN202111440936A CN114212276B CN 114212276 B CN114212276 B CN 114212276B CN 202111440936 A CN202111440936 A CN 202111440936A CN 114212276 B CN114212276 B CN 114212276B
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- pressing
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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 compression assembly (1), wherein the compression assembly is provided with a handle part and a compression part, the compression assembly is hinged to the upper part of a door frame assembly (2) at a position close to the compression part, the space station cabin door comprises a cabin door assembly (3), and the upper surface of the edge part of a sealing sleeve is in sealing tight contact with a sealing pressing block in a state that the space station cabin door is closed; the lower surface of the edge portion is in sealing close contact with the upper surface of the lower portion of the door frame assembly. The cabin door has the advantages that the sealing structure is simple, the operation is easy, and the sealing operation of the multistage sealing structure can be completed at one time only by manually rotating the compression assembly to the compression position; the assembling and adjusting method provided by the invention can remarkably reduce the assembling difficulty in assembling the sealing structure, and when an astronaut is on orbit, the sealing element can be adjusted to complete the assembly by simply installing, so that the assembling 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 capacity of a space station, and the structure form of the split type cabin door is different from that of a conventional integral sealed cabin door. The door body of the cabin door with the split space station is of a split assembly structure, the space station is required to be sent in the form of a part, and the space station is assembled in the space station running on the orbit by an astronaut.
Traditional cabin doors are assembled on the ground, and an astronaut is not required for on-orbit running of the assembly. The split cabin door is emitted in a spare part state, and the assembly is completed on the orbit by an astronaut; the traditional cabin door body is of an integral structure, the number of compression points is large, the split cabin door is of a door body assembly type structure, the number of compression points is only half of the number of compression points of the traditional cabin door, the number of compression points is small, and the rigidity of the whole 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 assembled and adjusted on the orbit by an astronaut, higher requirements are required for the assembly operation of the astronaut, and whether the sealing performance of the cabin door meets the sealing requirements after the assembly is completed is questionable. The following problems exist in the assembly and adjustment work of the sealing structure of the space station split cabin door aiming at the characteristics of the space station split cabin door:
because the split cabin door of the space station is transmitted to space in a part state, the space station needs to be assembled on-orbit by astronauts, and the difficulty of assembly operation of the astronauts is high; and the split cabin door of the space station with weak rigidity under the multi-constraint condition has a multi-stage sealing structure, and the assembling and adjusting working steps of the multi-stage sealing structure are complex and low in efficiency.
Disclosure of Invention
The invention solves the technical problems that: overcomes the defects of the prior art and provides a space station cabin door and an assembling and adjusting method of the space station cabin door sealing structure. The cabin door provided by the invention has a simple sealing structure and is easy to operate; the assembling difficulty in assembling the sealing structure can be remarkably reduced by using the assembling and adjusting method provided by the invention, the assembling steps are simple, and the efficiency is high. The difficulty of assembly operation of astronauts can be reduced.
In one aspect, a space station door according to the present invention includes a hold-down assembly having a handle portion and a hold-down portion, the hold-down assembly being hinged to an upper portion of a door frame assembly at a location proximate the hold-down portion, comprising:
a door assembly, in which an upper surface of the edge portion is in sealing close contact with a pressing portion of the pressing assembly in a state in which the space station door is closed; the lower surface of the edge portion is in sealing close contact with the upper surface of the lower portion of the door frame assembly.
The door frame assembly is fixedly arranged on the space station cabin body and is a mounting foundation of the space station cabin door. The compaction assemblies are uniformly distributed, and the edge parts of the cabin door assemblies are compacted to form compaction points. The compression force value at the compression point is the maximum compression force experienced by the overall door assembly. The center point is at the edge of the door assembly at the middle position between every two adjacent pressing points, and the pressing force value at the center point is the minimum value of the pressing force applied to the whole door assembly. In use, the space station cabin door can be tightly pressed and fixed on the space station cabin body in a medium-tight manner only by pulling the pressing component to the pressing position.
Further, the method comprises the steps of,
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 coated on the upper surface, the side edges and the lower surface of the edge part of the door body, wherein an opening is arranged on 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 repair plane, and a first annular protruding part and a second annular protruding part which are the same in height and concentric with each other are arranged at two ends of the other surface opposite to the repair plane; grooves are formed in the circle centers of the first protruding part and the second protruding part on the other surface of the sealing pressing block; the groove between the first bulge part and the second bulge part is a space for accommodating the boss, and the groove is positioned at the center of the sealing pressing block; the height of the groove is smaller than that of the boss; in a state that the space station cabin door is closed, the compression part of the compression assembly is in close contact with the repair plane; the first protruding part and the second protruding part are in tight contact with the sealing sleeve around the boss in a sealing way, and the upper surface of the boss is in tight contact with the bottom surface of the groove.
The sections of the first protruding part and the second protruding part are circular arcs 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 surface of the sealing pressing block. The cross section of the sealing sleeve is U-shaped, and the sealing sleeve is integrally formed. When the compression assembly is positioned at the compression position and the door body and the door frame assembly are in sealing connection, the first bulge part and the second bulge part of the sealing pressing block are in medium sealing abutting contact with the sealing sleeve on the upper surface of the edge part of the door body, and meanwhile the upper surface of the boss is rigidly and tightly contacted with the bottom surface of the groove. The sealing sleeve at the lower surface of the edge portion of the door body is in medium sealing abutting contact with the door frame assembly.
On the other hand, the method for adjusting the sealing structure of the cabin door of the space station comprises the following steps:
s1, reserving process allowance in the height direction when processing a boss and a sealing pressing block, and reserving process allowance in the height direction when processing a sealing pressing block tool piece;
s2, adopting a repairing method to repair the height of the boss, and ensuring that the seal between the seal pressing block and the seal sleeve meets the space station seal compression requirement and leakage rate requirement;
s3, after the door body assembly and the sealing sleeve are assembled, fixing a sealing pressing block tool piece onto the door body, and adjusting the compression amount of the sealing sleeve by using an increased or decreased tool gasket by adopting a repair method to obtain the sum of the heights of the sealing pressing block tool piece and the tool gasket, wherein the sum of the heights of the sealing pressing block tool piece and the tool gasket can ensure that the sealing between the door body and the door frame meets the space station sealing compression amount requirement and the leakage rate requirement, and repairing the height of a sealing pressing block according to the sum of the heights of the sealing pressing block tool piece and the tool gasket;
s4, replacing the sealing pressing block tool piece and the tool gasket with the sealing pressing block, assembling the space station cabin door, sealing the door body assembly with the door frame assembly by using the pressing assembly, measuring the sealing between the door body and the door frame to meet the space station sealing compression requirement and leakage rate requirement, and applying the operating force on the handle part of the pressing assembly to meet the requirement of the space human engineering system.
Through the steps, the high-precision sealing pressing block can be obtained, and the sealing pressing block is directly installed to the cabin door without any adjustment or processing when an astronaut is in orbit, so that the sealing requirement of the cabin door can be met.
Further, the method for installing and adjusting the sealing structure of the cabin door of the space station according to the invention further comprises the following steps:
s5, detaching the space station cabin door, recording the accurate height of the sealing pressing block, and making a mark with the corresponding boss.
The sealing pressing blocks which meet the sealing requirement and the leakage rate requirement after being tested are marked on the ground with the bosses on the door body, so that the sealing pressing blocks cannot be misplaced when an astronaut installs the sealing pressing blocks in orbit, and leakage accidents cannot be caused.
Further, the method for adjusting the sealing structure of the cabin door of the space station according to the present invention, in the step S2, comprises the following steps:
s21, calculating the boss height theoretical value by using a sealing compression rate formula;
s22, repairing the process allowance of the boss height according to the boss height theoretical value;
s23, after finishing the repair, measuring and recording the actual height of the boss, and carrying out seal compression rate recalculation according to the actual height of the boss to ensure that the design index is met.
The height of the boss after repair can be met, when the compression assembly is in a compression position, the upper surface of the boss is in rigid tight contact with the bottom surface of the groove, and meanwhile, the first protruding part and the second protruding part of the sealing pressing block compress the sealing sleeve around the boss by a certain compression amount. The value of a certain compression amount by which the sealing sleeve at the periphery of the boss is compressed is smaller than the thickness value b at the periphery of the opening of the sealing sleeve. At this time, the contact surface formed by rigidly and tightly contacting the upper surface of the boss with the bottom surface of the groove and the other surface of the sealing pressing block have no associated position relationship. That is, in the concept of the present invention, the height of the first protrusion and the height of the second protrusion are independent from each other and can be controlled separately from the depth of the groove.
Further, according to the method for adjusting the sealing structure of the cabin door of the space station,
in the step S21, the height values c of the first boss and the second boss of the sealing block and the thickness value b at the periphery of the opening of the sealing sleeve are actually measured, and then the theoretical boss height value a is obtained according to the design index delta of the sealing compression ratio between the sealing block and the sealing sleeve and the calculation formula delta= (b- (a-c))/b of the sealing compression ratio.
Further, according to the method for adjusting the sealing structure of the cabin door of the space station,
in the step S3, the repair plane is repaired when the sealing press block is repaired.
Further, according to the method for adjusting the sealing structure of the cabin door of the space station,
in the step S3, the following steps are included:
s31, gasket is arranged between the sealing pressing block tool piece and the pressing component, one gasket is arranged from the gasket, each gasket is added, the door body component and the door frame component are pressed through the pressing component, then the compression rate of the pressing point, the compression rate of the central point and the operation force of the pressing component are measured and calculated in sequence until the sum of the heights of the sealing pressing block tool piece and the added gasket in the pressing state enables the compression rate of the sealing sleeve to meet the sealing design requirement, and quick leak detection is carried out to ensure that the leakage rate meets the design requirement; wherein, the liquid crystal display device comprises a liquid crystal display device,
the compression points are contact points of the sealing pressing blocks and the door body, and the center points are positioned at the positions of the door body and the door frame assembly on the symmetrical center lines of the two adjacent compression points;
s32, in a compression state, the sum of the heights of the sealing pressing block tool piece and the increased gasket is the required actual height of the sealing pressing block, and the sealing pressing block is repaired according to the actual height.
Further, according to the method for adjusting the sealing structure of the cabin door of the space station,
in the step S31, the compression rate of the compression point and the compression rate of the central point are calculated by sequentially measuring the sealing gap d of the compression point and the corresponding position of the central point in a state that the compression assembly is in compression, and combining the sealing ring height h of the sealing sleeve, and obtaining the compression rate of the compression point and the compression rate of the central point according to a calculation formula delta= (h-d)/d of the compression rate of the sealing sleeve.
Further, according to the method for adjusting the sealing structure of the cabin door of the space station,
in the step S4, the method for measuring and calculating the compression rate of the compression point, the compression rate of the central point and the operation force of the compression assembly includes that the compression point and the sealing gap d at the corresponding position of the central point are sequentially measured when the compression assembly is in a compression state, and the compression rate of the compression point and the compression rate of the central point are obtained according to a formula delta= (h-d)/d calculated by combining the height h of the sealing ring of the sealing sleeve and the compression rate of the sealing sleeve; under the condition of compressing, the sealing pressing block enables the compression ratio of the sealing sleeve to meet the sealing design requirement, and quick leak detection is carried out to ensure that the leakage ratio meets the design requirement.
In the step S4, the method for measuring the operating force of the pressing assembly includes using a push-pull force meter to measure the pressing and unlocking operating forces perpendicular to the end of the handle of the pressing assembly.
Compared with the prior art, the invention has the following remarkable beneficial effects: the cabin door has the advantages that the sealing structure is simple, the operation is easy, and the sealing operation of the multistage sealing structure can be completed at one time only by manually rotating the compression assembly to the compression position; the assembling and adjusting method provided by the invention can remarkably reduce the assembling difficulty in assembling the sealing structure, and when an astronaut is on orbit, the sealing element can be adjusted to complete the assembly by simply installing, so that the assembling steps are simple and the efficiency is high. The difficulty of assembly operation of astronauts can be reduced.
Drawings
FIG. 1 is a flow chart of a method of installing and adjusting a space station hatch door seal structure according to one embodiment of the invention;
FIG. 2 is a partial cross-sectional view of a space station 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 one embodiment of the invention;
FIG. 4 is a schematic view showing the structure of a space station door according to one embodiment of the present invention;
fig. 5 is a schematic view of the structure of a space station door according to one embodiment of the present invention.
Figure number: 1-a compacting assembly; 11-a handle portion; 12-a pressing part; 2-door frame assembly; 3-door assembly; 31-door body; 31 a-boss; 32-sealing sleeve; 33-sealing the briquetting; 33 a-a repair 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 apparent that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
The present invention will be described in detail below with reference to the drawings and the specific embodiments, which are not described in detail herein, but the embodiments of the present invention are not limited to the following embodiments.
The structural features of the sealing press block tooling member according to the present invention are the same as those of the sealing press block 33, and the height dimension of the sealing press block tooling member is smaller than the design height dimension of the sealing press block 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 tool piece is firstly used for replacing the sealing press block 33 to be installed on the door body, and in the subsequent step, the sealing press block tool piece is replaced by the sealing press block 33.
As shown in fig. 2, 3, 4 and 5, a space station door of an embodiment of the present invention includes a compressing assembly 1, the compressing assembly 1 having a handle part 11 and a compressing part 12, the compressing assembly 1 being hinged to an upper part of a door frame assembly 2 at a position near the compressing part 12, including:
a door assembly 3 in which the repair plane 33a is in sealing close contact with the pressing portion 12 of the pressing assembly 1 in a state where the space station door is closed; the lower surface of the edge portion is in sealing close contact with the upper surface of the lower portion of the door frame assembly 2.
Further, the door assembly 3 comprises: the door body 31, the door body 31 is that the upper surface of the edge part of the door body 31 is provided with a boss 31a; a sealing sleeve 32, which 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 arranged on 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; and a sealing pressing block 33 fixedly installed on the door body 31 and located at an upper portion of the boss 31a; one surface of the sealing pressing block 33 is a repair plane 33a, and a first annular protruding part and a second annular protruding part which are the same in height and concentric circles are arranged at two ends of the other surface opposite to the repair plane 33 a; grooves are formed in the circle centers of the first protruding part and the second protruding part on the other surface of the sealing pressing block; the groove between the first protruding part and the second protruding part is a space for accommodating the boss 31a, and the groove is positioned at the center of the sealing pressing block 33; the height of the groove is smaller than the height of the boss 31a; in the state that the space station hatch door is closed, the compacting part 12 of the compacting assembly 1 is in close contact with the repair plane 33 a; the first and second protrusions are in tight contact with the sealing sleeve 32 around the boss 31a, and the upper surface of the boss 31a is in tight contact with the bottom surface of the groove. The first and second protrusions are circular in cross section and are annularly provided on the other surface of the seal pressing block 33. There is no associated positional relationship between the groove bottom surface of the groove and the other face of the seal pressing block 33.
Specifically, the door frame assembly 2 is circular and is fixedly mounted on the cabin. The hatch assembly 3 comprises a door body 31 and 3 sealing compacts 33. The door body 31 is composed of two semicircular door bodies 31, 3 bosses 31a are uniformly arranged at the edge of the door body 31, and 3 sealing pressing blocks 33 are fixedly arranged at the positions on the door body 31 matched with the 3 bosses 31 a. On the door frame assembly 2, 3 pressing assemblies 1 are hinged at positions to be matched with the 3 bosses 31 a. The sealing member covers the upper surface, side surfaces and lower surface of the edge portion of the door body 31.
As shown in fig. 1, in one embodiment of the present invention, a method for adjusting a sealing structure of a door of a space station includes the steps of:
s1, reserving process allowance in the height direction when machining a boss 31a and a sealing pressing block 33, and reserving process allowance in the height direction when machining a sealing pressing block tool piece;
further, the method for installing and adjusting the sealing structure of the cabin door of the space station according to the invention further comprises the following steps:
s2, repairing the height of the boss 31a by adopting a repairing method, so that the sealing between the sealing pressing block 33 and the sealing sleeve 32 is ensured to meet the requirements of the sealing compression amount and the leakage rate of the space station.
In particular to a method for adjusting a sealing structure of a cabin door of a space station,
in step S2, the following steps are included:
s21, calculating a theoretical height value of the boss 31a by using a sealing compression rate formula;
in step S21, the height value c of the first boss and the second boss of the sealing pressing block 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= (b- (a-c))/b of the sealing compression rate according to the sealing compression rate design index δ between the sealing pressing block 33 and the sealing sleeve 32.
S22, repairing the process allowance of the height of the boss 31a according to the theoretical value of the height of the boss 31a;
s23, after finishing the repair, measuring and recording the actual height of the boss 31a, and carrying out seal compression rate recalculation according to the actual height of the boss 31a to ensure that the design index is met.
The height of the boss 31a after repair can be satisfied, when the compression assembly 1 is in the compression position, the upper surface of the boss 31a is in rigid and tight contact with the bottom surface of the groove, and the first and second protrusions of the sealing press 33 compress the sealing sleeve around the boss 31a by a certain compression amount, wherein the value of the certain compression amount by which the sealing sleeve around the boss 31a is compressed is smaller than the thickness value b at the periphery of the opening of the sealing sleeve. At this time, a contact surface formed by rigidly and closely contacting the upper surface of the boss 31a with the bottom surface of the groove and a connection surface formed by connecting the boss 31a with the seal pressing block 33 have no positional relationship with each other.
Further, the method for installing and adjusting the sealing structure of the cabin door of the space station according to the invention further comprises the following steps:
s3, after the assembly of the door body 31 assembly and the sealing sleeve 32 is completed, fixing the sealing pressing block tool piece onto the door body 31, and adopting a repair method, and adjusting the compression amount of the sealing sleeve 32 by increasing or reducing the tool gaskets to obtain the sum of the heights of the sealing pressing block tool piece and the tool gaskets, wherein the sealing between the door body 31 and the door frame can be ensured to meet the space station sealing compression amount requirement and the leakage rate requirement, and the height of the sealing pressing block 33 is repaired according to the sum of the heights of the sealing pressing block tool piece and the tool gaskets.
Specifically, in step S3, the repair flat surface 33a is repaired when the seal pressing block 33 is repaired.
In step S3, the following steps are included:
s31, gasket is filled between the sealing pressing tool piece and the pressing assembly 1, one gasket is filled, one gasket is added from the gasket filling, the door body 31 assembly and the door frame assembly 2 are pressed by the pressing assembly 1, then the compression rate of the pressing point, the compression rate of the central point and the operation force of the pressing assembly 1 are measured and calculated in sequence until the sum of the heights of the sealing pressing tool piece and the added gasket in the pressing state enables the compression rate of the sealing sleeve 32 to meet the sealing design requirement, quick leak detection is carried out to ensure that the leak rate meets the design requirement,
the pressing points are the contact points of the sealing pressing block 33 and the door body 31, and the center point is positioned at 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 rate of the compression point and the compression rate of the center point are calculated by sequentially measuring the sealing gap d at the corresponding position of the compression point and the center point of the compression assembly 1 in the compression state, and combining the sealing ring height h of the sealing sleeve 32, and obtaining the compression rate of the compression point and the compression rate of the center point according to a calculation formula delta= (h-d)/d of the compression rate of the sealing sleeve.
S32, in a compressed state, the sum of the height of the sealing pressing block tool piece and the height of the increased gasket is the required actual height of the sealing pressing block 33, and the sealing pressing block 33 is repaired according to the actual height.
Further, the method for installing and adjusting the sealing structure of the cabin door of the space station according to the invention further comprises the following steps:
s4, replacing the sealing pressing block tool piece and the tool gasket by using the sealing pressing block 33, assembling the space station cabin door, sealing the door body 31 assembly and the door frame assembly 2 by using the pressing assembly 1, measuring the sealing between the door body 31 and the door frame to meet the space station sealing compression requirement and leakage rate requirement, and applying the operating force to the handle part 11 of the pressing assembly 1 to meet the requirement of the space human engineering system.
Specifically, in step S4, the method for measuring and calculating the compression rate of the compression point, the compression rate of the central point, and the operation force of the compression assembly 1 is that, in the state that the compression assembly 1 is in compression, the compression point is sequentially measured, the sealing gap d at the position corresponding to the central point is combined with the sealing ring height h of the sealing sleeve 32, and the compression rate of the compression point and the compression rate of the central point are obtained according to the calculation formula delta= (h-d)/d of the compression rate of the sealing sleeve; in the compressed state, the sealing pressing block 33 is required to enable the compression ratio of the sealing sleeve 32 to meet the sealing design requirement, and quick leak detection is performed to ensure that the leakage ratio meets the design requirement.
In step S4, the pressing force of the pressing assembly 1 is measured by using a push-pull force meter perpendicular to the end of the handle of the pressing assembly 1, and the pressing and unlocking forces are measured respectively.
Further, the method for installing and adjusting the sealing structure of the cabin door of the space station according to the invention further comprises the following steps:
s5, disassembling the space station cabin door, recording the accurate height of the sealing pressing block 33, and making a mark with the corresponding boss 31 a.
In one embodiment of the present invention, as shown in fig. 3, first, a sufficient process margin of 3 bosses 31a is reserved in the 2 semicircular door body 31 part processing stage; a sufficient height of process margin is reserved at the 3 seal compact 33 part machining stages. Meanwhile, 3 sealing pressing block tool pieces are designed and processed, the structural characteristics are the same as those of the 3 sealing pressing blocks 33, and the height dimension of the 3 sealing pressing block tool pieces is smaller than the design height of the 3 sealing pressing blocks 33.
With respect to the sealing structure between the sealing pressing block 33 and the sealing sleeve 32 shown in fig. 3, the sealing between the sealing pressing block 33 and the sealing sleeve 32 is achieved by controlling the height of the boss 31a of the door body 31. The equation delta= (b- (a-c))/b is calculated according to the sealing compression ratio, and the theoretical height value a= (1-delta) b+c of the boss 31a of the door body 31 is calculated by actually measuring the height c of the first protruding part and the second protruding part of the sealing pressing block 33 and the thickness value b of the sealing sleeve 32 and combining the sealing compression ratio design value delta. 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 machining precision. By measuring the height of the boss 31a of the door body 31 after the repair processing, substituting the sealing compression rate calculation formula delta= (b- (a-c))/b, respectively calculating the actual sealing compression rate value of the sealing structure between the sealing pressing block 33 and the sealing sleeve 32, and judging that the structural sealing compression rate design index requirement should be met.
And (3) assembling the sealing cabin door, namely assembling the sealing sleeve 32 in place after assembling the 2 semicircular door bodies 31, assembling the sealing press block tool pieces of the 3 sealing press blocks 33, and assembling the 3 pressing assemblies 1.
The overall sealing structure of the door body 31 between the door assembly 3 and the door frame assembly 2 shown in fig. 2 is that sealing between the sealing sleeve 32 and the door frame assembly 2, tooling gaskets are added between the sealing pressing tooling pieces of the 3 sealing pressing blocks 33 and the 3 pressing assemblies 1, under the state that the 3 pressing assemblies 1 are in a pressing state, 3 pressing points are sequentially measured, sealing gaps d at positions corresponding to the 3 center points are combined with the sealing ring height h of the sealing sleeve 32, a formula delta= (h-d)/d is calculated according to the sealing compression rate to obtain the 3 pressing point compression rate and the 3 center point compression rate, a push-pull force meter is used for measuring the pressing and unlocking operation forces perpendicular to the tail end of the handle part 11 of the 3 pressing assemblies 1, and whether all the design requirements are met is judged, and the thickness of the 3 pressing point tooling gaskets is adjusted until the 3 pressing point compression rate, the 3 center point compression rate and the 3 pressing assembly 1 operation force meet the design index requirements. And (3) 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 values of the 3 sealing pressing block tool pieces and the tool gaskets at the moment. And according to the total height value of the 3 sealing pressing block tool parts and the tool gasket, milling and repairing the 3 sealing pressing blocks 33 at the 3 pressing points respectively, and strictly controlling the machining precision. And 3 sealing press blocks 33 after processing are used for replacing 3 sealing press block tool pieces and tool gaskets, and are arranged on the cabin door assembly 3, 3 compression points, 3 center point compression rates and 3 operation forces of the compression assembly 1 are retested, quick leak detection is performed, and all indexes are judged to meet design requirements. 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 door is disassembled into parts, the accurate heights of 3 pressing blocks are recorded, and the parts are made into marks with the corresponding 3 bosses 31 a. So that the astronaut can identify the correct installation positions of the 3 pressing blocks during on-orbit installation.
The cabin door in one embodiment of the invention has the advantages of simple sealing structure and easy operation, and can finish the sealing operation of the multi-stage sealing structure at one time only by manually rotating the compression assembly 1 to the compression position; the assembling difficulty in assembling the sealing structure can be remarkably reduced by using the assembling and adjusting method in one embodiment provided by the invention, and the tooling gasket is not required to be sent to a space station. When the astronaut is on the orbit, the number and the thickness of the tooling gaskets do not need to be adjusted on the orbit, the assembly can be completed only by simple installation and adjustment of the sealing pressing block 33, the assembly steps are simple, and the efficiency is high. The difficulty of assembly operation of astronauts can be reduced.
The foregoing is merely exemplary of embodiments of the invention and, as regards devices and arrangements not explicitly described in this disclosure, it should be understood that this can be done by general purpose 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, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. A space station hatch door comprising a compression assembly (1), the compression assembly (1) having a handle portion (11) and a compression portion (12), the compression assembly (1) being hinged to an upper portion of a door frame assembly (2) at a position proximate to the compression portion (12), characterized by comprising:
a door assembly (3) in which an upper surface of the edge portion is in sealing close contact with a pressing portion (12) of the pressing assembly (1) in a state in which the space station door is closed; the lower surface of the edge part is in sealing close contact with the upper surface of the lower part of the door frame assembly (2);
the door assembly (3) comprises:
a door body (31), wherein a boss (31 a) is arranged on the upper surface of the edge part of the door body (31);
the sealing sleeve (32) is coated on the upper surface, the side edges 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 (31 a) is exposed from the opening; and
a sealing pressing block (33) fixedly mounted on the door body (31) and positioned at the upper part of the boss (31 a); one surface of the sealing pressing block (33) is a repair plane (33 a), and a first annular protruding part and a second annular protruding part which are the same in height and concentric with each other are arranged at two ends of the other surface opposite to the repair plane (33 a); the other surface of the sealing pressing block is provided with a groove at the circle center of the first bulge part and the circle center of the second bulge part, the groove is a space for accommodating the boss (31 a), and the groove is positioned at the center of the sealing pressing block (33); the height of the groove is smaller than the height of the boss (31 a); in the closed state of the space station hatch, the compacting part (12) of the compacting assembly (1) is in close contact with the repair plane (33 a); the first and second protrusions are in sealing close contact with a sealing sleeve (32) around the boss (31 a); the upper surface of the boss (31 a) is in close contact with the bottom surface of the groove.
2. A method of installing and adjusting a space station door seal according to claim 1, comprising the steps of:
s1, reserving process allowance in the height direction when machining a boss (31 a) and a sealing pressing block (33), and reserving process allowance in the height direction when machining a sealing pressing block tool piece;
s2, adopting a repairing method to repair the height of the boss (31 a) so as to ensure that the seal between the seal pressing block (33) and the seal sleeve (32) meets the space station seal compression requirement and leakage rate requirement;
s3, after the assembly of the door body (31) and the sealing sleeve (32) is completed, fixing a sealing pressing block tool piece onto the door body (31), and adopting a repair method to adjust the compression amount of the sealing sleeve (32) by increasing or reducing tool gaskets to obtain the sum of the heights of the sealing pressing block tool piece and the tool gaskets, wherein the sum of the heights of the sealing pressing block tool piece and the tool gaskets can ensure that the sealing between the door body (31) and the door frame meets the space station sealing compression amount requirement and the leakage rate requirement, and repairing the height of a sealing pressing block (33) according to the sum of the heights of the sealing pressing block tool piece and the tool gaskets;
s4, replacing a sealing pressing block tool piece and a tool gasket by using a sealing pressing block (33), completing assembly of the space station cabin door, sealing the door body (31) assembly and the door frame assembly (2) by using the pressing assembly (1), measuring the sealing between the door body (31) and the door frame to meet the space station sealing compression amount requirement and leakage rate requirement, and applying the operating force on the handle part (11) of the pressing assembly (1) to meet the requirement of an aerospace human engineering system;
s5, detaching the space station cabin door, recording the accurate height of the sealing pressing block (33), and making a mark with the corresponding boss (31 a).
3. The method for installing and adjusting the sealing structure of the cabin door of the space station according to claim 2, wherein,
in the step S2, the following steps are included:
s21, calculating a theoretical height value of the boss (31 a) by using a sealing compression rate formula;
s22, repairing the process allowance of the height of the boss (31 a) according to the theoretical value of the height of the boss (31 a);
s23, after finishing the repair, measuring and recording the actual height of the boss (31 a), and carrying out seal compression rate recalculation according to the actual height of the boss (31 a) to ensure that the design index is met.
4. A method for adjusting a sealing structure of a door of a space station according to claim 3,
in the step S21, first, the height values c of the first and second protrusions of the sealing block (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 (31 a) is obtained from the calculation formula δ= (b- (a-c))/b of the sealing compression ratio according to the sealing compression ratio design index (δ) between the sealing block (33) and the sealing sleeve (32).
5. The method for installing and adjusting the sealing structure of the cabin door of the space station according to claim 2, wherein,
in step S3, the repair plane (33 a) is repaired when the sealing pressing block (33) is repaired.
6. The method for installing and adjusting the sealing structure of the cabin door of the space station according to claim 5, wherein,
in the step S3, the following steps are included:
s31, between the sealing pressing tool piece and the pressing component (1), gasket is arranged, from gasket arrangement, each gasket is added, the door body (31) component and the door frame component (2) are pressed by the pressing component (1), then the compression rate of the pressing point, the compression rate of the central point and the operation force of the pressing component (1) are measured and calculated in sequence until the sum of the heights of the sealing pressing tool piece and the added gasket in the pressing state enables the compression rate of the sealing sleeve (32) to meet the sealing design requirement, quick leak detection is carried out to ensure that the leakage rate meets the design requirement,
the compression points are contact points of the sealing pressing blocks (33) and the door body (31), and the center points are positioned at the positions of the door body (31) and the door frame assembly (2) on the symmetrical center lines of the two adjacent compression points;
s32, in a pressing state, the sum of the heights of the sealing pressing block tool piece and the increased gasket is the required actual height of the sealing pressing block (33), and the sealing pressing block (33) is repaired according to the actual height.
7. The method for installing and adjusting the sealing structure of the cabin door of the space station according to claim 6, wherein,
in the step S31, the compression rate of the compression point and the compression rate of the central point are calculated by sequentially measuring the compression point and the sealing gap (d) at the corresponding position of the central point of the compression assembly (1) in the compression state, and combining the sealing ring height (h) of the sealing sleeve (32), and obtaining the compression rate of the compression point and the compression rate of the central point according to a calculation formula delta= (h-d)/d of the compression rate of the sealing.
8. The method for installing and adjusting the cabin door sealing structure of the space station according to claim 2, wherein in the step S4, the compression rate of the compression point, the compression rate of the central point and the operation force of the compression assembly (1) are measured and calculated, namely, the compression assembly (1) is in a compression state, the sealing gap (d) at the corresponding position of the compression point and the central point is sequentially measured, the sealing ring height (h) of the sealing sleeve (32) is combined, and the compression rate of the compression point and the compression rate of the central point are obtained according to a calculation formula delta= (h-d)/d of the compression rate of the sealing sleeve (32) according to the calculation formula delta= (h-d), and the compression rate of the sealing block (33) is required to meet the sealing design requirement in the compression state, and quick leak detection is performed to ensure that the leakage rate meets the design requirement;
in the step S4, the method for measuring the operating force of the pressing assembly (1) includes using a push-pull force meter to measure the pressing and unlocking operating forces perpendicular to the end of the handle of the pressing assembly (1).
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Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4898348A (en) * | 1988-12-30 | 1990-02-06 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Docking system for spacecraft |
| RU2170803C2 (en) * | 1999-04-27 | 2001-07-20 | Таганрогский авиационный научно-технический комплекс им. Г.М. Бериева Открытое акционерное общество | Device for sealing-up doors and hatches of seaplanes |
| FR2829722A1 (en) * | 2001-09-17 | 2003-03-21 | Cmpe | Aircraft door seal repair procedure using on-site equipment with heated clamp to over mould damaged portion |
| CN1923620A (en) * | 2006-09-07 | 2007-03-07 | 北京航空航天大学 | Switch operating equipment for space capsule door |
| WO2011148167A2 (en) * | 2010-05-27 | 2011-12-01 | Airbus Operations Limited | Method of sealing a gap |
| CN102507106A (en) * | 2011-11-21 | 2012-06-20 | 北京卫星环境工程研究所 | Method for monitoring leakage in on-orbit state for spacecraft |
| CN102635298A (en) * | 2012-03-30 | 2012-08-15 | 长治清华机械厂 | Movable type escape capsule emergency escape door for mine |
| CN103527788A (en) * | 2013-10-22 | 2014-01-22 | 中国北方车辆研究所 | Combination type sealing gasket |
| CN204433027U (en) * | 2014-12-19 | 2015-07-01 | 成都飞机设计研究所 | Aircraft door hermetically-sealed construction |
| CN105095638A (en) * | 2015-03-25 | 2015-11-25 | 北京空间技术研制试验中心 | Leak rate design method for sealed cabin of manned spacecraft |
| CN106005359A (en) * | 2016-06-16 | 2016-10-12 | 沈阳飞机工业（集团）有限公司 | Airplane hatch cover connecting lock mounting method based on digital measurement |
| CN106195135A (en) * | 2016-07-15 | 2016-12-07 | 上海宇航系统工程研究所 | The hatch door locking of a kind of space and the manual driving device unlocked |
| CN107323649A (en) * | 2017-05-18 | 2017-11-07 | 上海空间推进研究所 | Airborne vehicle cabin door sealing structure |
| CN207598909U (en) * | 2017-11-30 | 2018-07-10 | 航天材料及工艺研究所 | A kind of chamfering sealing structure easy to plug |
| CN109323077A (en) * | 2018-11-02 | 2019-02-12 | 北京卫星制造厂有限公司 | It is a kind of can in-orbit rapid-maintenance sealing denoising structure |
| CN109339672A (en) * | 2018-11-20 | 2019-02-15 | 上海米开罗那机电技术有限公司 | A kind of transition door compacting sealing mechanism |
| CN110282158A (en) * | 2019-06-20 | 2019-09-27 | 北京机械设备研究所 | A kind of the space station quick take-up of hard shell water tank and elastic method |
| CN111605731A (en) * | 2020-04-30 | 2020-09-01 | 北京空间飞行器总体设计部 | Manned spacecraft large-drift-diameter rectangular sealed cabin door device |
| CN112647785A (en) * | 2020-12-17 | 2021-04-13 | 中航沈飞民用飞机有限责任公司 | Elastic structure for closing and limiting cabin door |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7325771B2 (en) * | 2004-09-23 | 2008-02-05 | The Boeing Company | Splice joints for composite aircraft fuselages and other structures |
| US7118069B2 (en) * | 2004-12-02 | 2006-10-10 | The Boeing Company | Integrated window belt system for aircraft cabins |
| US8091831B2 (en) * | 2006-11-28 | 2012-01-10 | Airbus Deutschland Gmbh | Aircraft with door seal arrangement |
| FR2999154B1 (en) * | 2012-12-12 | 2014-11-28 | Aircelle Sa | ASSEMBLY CENTER FOR TURBOREACTOR NACELLE |
| US8844750B1 (en) * | 2013-03-14 | 2014-09-30 | Arthur Richard Daniel Thompson | Hingeless door system for pressure vessels |
-
2021
- 2021-11-30 CN CN202111440936.2A patent/CN114212276B/en active Active
Patent Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4898348A (en) * | 1988-12-30 | 1990-02-06 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Docking system for spacecraft |
| RU2170803C2 (en) * | 1999-04-27 | 2001-07-20 | Таганрогский авиационный научно-технический комплекс им. Г.М. Бериева Открытое акционерное общество | Device for sealing-up doors and hatches of seaplanes |
| FR2829722A1 (en) * | 2001-09-17 | 2003-03-21 | Cmpe | Aircraft door seal repair procedure using on-site equipment with heated clamp to over mould damaged portion |
| CN1923620A (en) * | 2006-09-07 | 2007-03-07 | 北京航空航天大学 | Switch operating equipment for space capsule door |
| WO2011148167A2 (en) * | 2010-05-27 | 2011-12-01 | Airbus Operations Limited | Method of sealing a gap |
| CN102507106A (en) * | 2011-11-21 | 2012-06-20 | 北京卫星环境工程研究所 | Method for monitoring leakage in on-orbit state for spacecraft |
| CN102635298A (en) * | 2012-03-30 | 2012-08-15 | 长治清华机械厂 | Movable type escape capsule emergency escape door for mine |
| CN103527788A (en) * | 2013-10-22 | 2014-01-22 | 中国北方车辆研究所 | Combination type sealing gasket |
| CN204433027U (en) * | 2014-12-19 | 2015-07-01 | 成都飞机设计研究所 | Aircraft door hermetically-sealed construction |
| CN105095638A (en) * | 2015-03-25 | 2015-11-25 | 北京空间技术研制试验中心 | Leak rate design method for sealed cabin of manned spacecraft |
| CN106005359A (en) * | 2016-06-16 | 2016-10-12 | 沈阳飞机工业（集团）有限公司 | Airplane hatch cover connecting lock mounting method based on digital measurement |
| CN106195135A (en) * | 2016-07-15 | 2016-12-07 | 上海宇航系统工程研究所 | The hatch door locking of a kind of space and the manual driving device unlocked |
| CN107323649A (en) * | 2017-05-18 | 2017-11-07 | 上海空间推进研究所 | Airborne vehicle cabin door sealing structure |
| CN207598909U (en) * | 2017-11-30 | 2018-07-10 | 航天材料及工艺研究所 | A kind of chamfering sealing structure easy to plug |
| CN109323077A (en) * | 2018-11-02 | 2019-02-12 | 北京卫星制造厂有限公司 | It is a kind of can in-orbit rapid-maintenance sealing denoising structure |
| CN109339672A (en) * | 2018-11-20 | 2019-02-15 | 上海米开罗那机电技术有限公司 | A kind of transition door compacting sealing mechanism |
| CN110282158A (en) * | 2019-06-20 | 2019-09-27 | 北京机械设备研究所 | A kind of the space station quick take-up of hard shell water tank and elastic method |
| CN111605731A (en) * | 2020-04-30 | 2020-09-01 | 北京空间飞行器总体设计部 | Manned spacecraft large-drift-diameter rectangular sealed cabin door device |
| CN112647785A (en) * | 2020-12-17 | 2021-04-13 | 中航沈飞民用飞机有限责任公司 | Elastic structure for closing and limiting cabin door |
Non-Patent Citations (1)
| Title |
|---|
| Performance Prediction of Hatch Cover Drive Assembly in Space Environment;PAN BO;IEEE Access(Volume:7);156129-156135 * |
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