CN112483521A - Tool and method for sleeving rigid thermal protection layer on unclosed equal-diameter revolving body cabin section - Google Patents
Tool and method for sleeving rigid thermal protection layer on unclosed equal-diameter revolving body cabin section Download PDFInfo
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- CN112483521A CN112483521A CN202011284783.2A CN202011284783A CN112483521A CN 112483521 A CN112483521 A CN 112483521A CN 202011284783 A CN202011284783 A CN 202011284783A CN 112483521 A CN112483521 A CN 112483521A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B11/00—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding
- F16B11/006—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding by gluing
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention relates to the technical field of thermal protection materials, in particular to a tool and a method for sleeving a rigid thermal protection layer on a non-closed constant-diameter revolving body cabin section. This frock includes the bottom plate, preceding extension, back extension, many stands and at least one sliding die, the one end of stand is connected perpendicularly in the bottom plate, preceding extension and back extension are installed respectively at the front end and the rear end of cabin section, the sliding die is installed at the stand, and can follow the axial displacement of stand, and can radially carry out certain adjustment, can guarantee the whole profile degree of heat inoxidizing coating in certain extent, and can avoid interfering the region, thereby avoid damaging the cabin body or heat inoxidizing coating, in addition, at the in-process of suit heat inoxidizing coating, need not extra location frock, can cup joint heat inoxidizing coating at non-closed constant diameter solid of revolution cabin section high-efficiently and accurately, and simple structure, and convenient operation. The method uses the tool for auxiliary installation, is simple and convenient to implement, has strong operability, and is suitable for batch production.
Description
Technical Field
The invention relates to the technical field of thermal protection materials, in particular to a tool and a method for sleeving a rigid thermal protection layer on a non-closed constant-diameter revolving body cabin section.
Background
When the hypersonic aircraft is cruising at a high speed for a long time in the atmosphere, the surface of the hypersonic aircraft bears more severe heat load action and airflow scouring action.
The heat insulation scheme of the prophase aircraft is mainly to prepare a heat protection material in blocks and then bond the heat protection material on the surface of the aircraft block by block. The problems of the method are that: gaps are generated at the splicing positions of the thermal protection materials difficultly, more heat is transferred to the interior of the aircraft, and hidden danger is brought to normal operation of components; on the other hand, when in bonding, all the thermal protection materials need to be aligned and positioned, the requirement on the profile tolerance of the aircraft is high, the assembly process is complex, the difficulty is high, and the efficiency is low.
Aiming at the problems of the scheme of preparing and bonding the heat-insulating material in blocks, a method for forming the heat-insulating material on the cabin section in situ is developed, which comprises the following steps: and (3) taking the cabin section as a male die of a forming die, sleeving a fiber reinforced framework outside the cabin section, integrally assembling the cabin section and the fiber reinforced framework in the female die, injecting glue solution into a die cavity, and curing to obtain the integral thermal protection layer. Although the method avoids excessive splicing seams in the blocking scheme, certain problems still exist: the preparation of the thermal protection layer and the preparation of the cabin section cold structure cannot be performed in parallel, and the production of the thermal protection layer can be performed only after the cold structure is processed, so that the production efficiency is low; in addition, when the thermal protection layer is prepared, the cabin section can experience temperature and pressure changes and the like together with glue solution, certain risks exist, and once the cabin section is damaged, the task progress of a product is seriously influenced.
Therefore, the prior art applies a rigid thermal protective material formed by integrally forming a female die and a male die, which is rigid and has slight deformation capability. The device can be sleeved on a non-closed equal-diameter revolving body cabin section in theory, so that the problems of multiple gaps, high assembly difficulty and low efficiency of a blocking scheme can be solved, and the problems that a hot protective layer and a cabin cold structure preparation of an in-situ forming scheme cannot be parallel and the cabin is at a risk of damage can be solved.
But unclosed isometric solid of revolution cabin section, its cross section is "C" type on an average, generally for machining or weld forming's metal material, and during weld forming, the profile tolerance is difficult to guarantee, has the risk of out of tolerance, can cause the product to damage even to the isometric solid of revolution cabin section, when cup jointing, take place the frictioning phenomenon easily between thermal protection layer and the cabin section, how high-efficient accurate cup joint the thermal protection layer in unclosed isometric solid of revolution cabin section is the current problem that needs to solve urgently.
Disclosure of Invention
Technical problem to be solved
The invention aims to provide a tool for sleeving a rigid thermal protection layer on a non-closed constant-diameter revolving body cabin section, which is used for assisting in realizing efficient sleeving assembly of the rigid thermal protection layer on the non-closed constant-diameter revolving body cabin section and solving at least one problem in the background art. .
The second objective of the present invention is to provide a method for sleeving a rigid thermal protection layer on a non-closed constant-diameter revolving body cabin section, so as to implement sleeving assembly of the rigid thermal protection layer on the non-closed constant-diameter revolving body cabin section, and solve at least one problem in the foregoing background art.
(II) technical scheme
In order to achieve the first object, in a first aspect, the invention provides a tool for sleeving a rigid thermal protection layer on a non-closed constant-diameter revolving body cabin section,
the method comprises the following steps:
a base plate;
the number of the upright columns is multiple, and one ends of the upright columns are vertically connected to the bottom plate;
the front extension part is arranged at the front end of the cabin section and is used for extending the axial length of the front end of the cabin section;
one end of the rear extension part is installed at the rear end of the cabin section, and the other end of the rear extension part is connected with the bottom plate and used for extending the axial length of the rear end of the cabin section; and
at least one sliding die, the sliding die includes first side mould and second side mould, first side mould includes first axial sliding portion and first radial sliding portion, first axial sliding portion installs at least one the stand, and can follow the axial displacement of stand, first radial sliding portion installs first axial sliding portion, and can follow the radial movement of stand, second side mould includes second axial sliding portion and second radial sliding portion, second axial sliding portion installs at least one the stand, and can follow the axial displacement of stand, second radial sliding portion installs second axial sliding portion, and can follow the radial movement of stand, work as first side mould with during the compound die of second side mould, first radial sliding portion with the butt joint of second radial sliding portion forms accommodation space, used for accommodating the cabin section sleeved with the thermal protection layer.
Preferably, the number of the upright posts is four;
the first axial sliding portion is mounted on two of the columns, and the second axial sliding portion is mounted on the other two of the columns.
Preferably, the slide die includes a plurality of slide dies, and the plurality of slide dies are mounted on the pillar in an axial direction of the pillar.
Preferably, the first axial sliding part is provided with at least one first through hole for penetrating the upright post;
a plurality of first adjusting holes are formed in at least one upright post used for mounting the first axial sliding part, the first adjusting holes are arranged at intervals along the axial direction of the upright post, and the position of the first side die in the axial direction of the upright post is fixed through the matching of a first adjusting pin and the first adjusting holes;
the second axial sliding part is provided with at least one second through hole for penetrating the upright post;
a plurality of second adjusting holes are formed in at least one upright post used for mounting the second axial sliding part, the second adjusting holes are arranged at intervals along the axial direction of the upright post, and the position of the second side die in the axial direction of the upright post is fixed through the matching of a second adjusting pin and the second adjusting holes; and/or
The first axial sliding part is provided with a first mounting hole for mounting the first radial sliding part, the first radial sliding part can slide in the first mounting hole along the radial direction of the upright column, the first axial sliding part is also provided with a first radial adjusting screw hole perpendicular to the first mounting hole, and the first adjusting bolt is matched with the first radial adjusting screw hole and used for fixing the position of the first radial sliding part;
the second axial sliding portion is provided with a second mounting hole used for mounting the second radial sliding portion, the second radial sliding portion can be arranged along the radial direction of the stand column and can slide in the second mounting hole, the second axial sliding portion is further provided with a second radial adjusting screw hole perpendicular to the second mounting hole, and the second adjusting bolt is matched with the second radial adjusting screw hole and used for fixing the position of the second radial sliding portion.
Preferably, a plurality of positioning portions extending in the radial direction are arranged in the circumferential direction of the rear extension portion and used for circumferentially positioning the thermal protection layer.
In order to achieve the second object, the invention also provides, in a second aspect, a method for sleeving a rigid thermal protection layer on a non-closed constant-diameter revolving body cabin section, wherein auxiliary installation is performed by using any one of the first aspects,
the method comprises the following steps:
respectively carrying out three-coordinate scanning on the inner molded surface of the thermal protection layer and the outer molded surface of the cabin section;
step two, comparing the data scanned twice in the step one to obtain the maximum gap amount between the thermal protection layer and the cabin section, and calculating the glue consumption;
thirdly, the front extension part and the rear extension part are respectively arranged at the front end and the rear end of the cabin section, and the cabin section is arranged on the bottom plate through the rear extension part;
gluing the outer molded surface of the cabin section and the inner molded surface of the thermal protection layer;
sleeving the thermal protection layer on the cabin section to perform axial and circumferential positioning;
sixthly, adjusting the position of the sliding die;
and step seven, dismantling the tool after the glue solution is cured.
Preferably, when the data is compared in the second step, the outer profile contour of the cabin segment is used as a reference, a clearance cloud map is obtained through three-coordinate data comparison, a clearance area and an interference area of the thermal protection layer and the cabin segment are distinguished, the interference area needing to be avoided is marked, and the sliding die is adjusted to avoid the marked interference area.
Preferably, if the interference region satisfies a + T > b + T, marking the interference region;
wherein a is the actual profile of the cabin section of the interference region, T is the actual thickness of the thermal protection layer of the interference region, b is the theoretical maximum positive deviation of the thermal protection layer, and T is the sum of the theoretical thicknesses of the thermal protection layer and the adhesive layer.
Preferably, in the fifth step, the thermal protection layer is sleeved in front of the cabin section, the non-product area of the thermal protection layer is axially cut, and when in sleeving, a proper force is applied to slightly break the thermal protection layer in the circumferential direction and then the thermal protection layer is sleeved in the cabin section;
and dropping the rear end of the thermal protection layer onto the bottom plate for axial positioning.
Preferably, a plurality of radially protruding positioning portions are arranged in the circumferential direction of the rear extension portion, and the thermal protection layer is circumferentially positioned by the positioning portions.
(III) advantageous effects
The technical scheme of the invention has the following advantages:
1. the tool for sleeving the rigid thermal protection layer on the cabin section of the non-closed constant-diameter revolving body comprises a bottom plate, a front extending part, a rear extending part, a plurality of stand columns and at least one sliding die, wherein one ends of the stand columns are vertically connected to the bottom plate, the front extending part and the rear extending part are respectively installed at the front end and the rear end of the cabin section, the sliding die is installed on the stand columns and can move along the axial direction of the stand columns and be adjusted in a radial direction, the overall profile of the thermal protection layer can be guaranteed within a certain range, and an interference area can be avoided, so that the cabin body or the thermal protection layer is prevented from being damaged.
2. The axial position of the sliding die is adjusted and positioned through the matching of the adjusting pin and the adjusting hole, the position of a radial sliding part of the sliding die is adjusted through the matching of the adjusting bolt and the adjusting screw hole, and the sliding die can be conveniently adjusted.
3. The sliding dies are arranged, the segmented positioning of the thermal protection layer is realized by adjusting the positions of the sliding dies, the interference position can be avoided while the overall profile degree is ensured as much as possible, the cabin body is prevented from being damaged by interference, and the profile degree after the thermal protection layer is sleeved can be ensured to the maximum extent.
4. The method for sleeving the rigid thermal protection layer on the unclosed equal-diameter revolving body cabin section has the advantages that the tool is used for auxiliary installation, the implementation is simple and convenient, the operability is strong, and the method is suitable for batch production.
Drawings
The drawings of the present invention are provided for illustrative purposes only, and the proportion and the number of the components in the drawings do not necessarily correspond to those of an actual product.
Fig. 1 is a schematic structural view of a tooling in which a rigid thermal protection layer is sleeved on a non-closed constant-diameter revolving body cabin section according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a tooling for sleeving a rigid thermal protection layer on a non-closed constant-diameter revolving body cabin section according to a second embodiment of the present invention;
fig. 3 is an exploded structural view of a fixture in which a rigid thermal protection layer is sleeved on a non-closed constant-diameter revolving body cabin section according to a second embodiment of the present invention;
fig. 4 is a schematic structural view of a tooling in which a rigid thermal protection layer is sleeved on a non-closed constant-diameter revolving body cabin section in the third embodiment of the present invention;
FIG. 5 is a schematic diagram of a method for marking an interference region according to a fourth embodiment of the present invention.
In the figure: 1: a base plate; 11: an annular projection; 2: a column; 3: a front extension; 4: a rear extension portion; 41: a positioning part; 5: a cabin section; 6: a first side mold; 61: a first axial sliding portion; 62: a first radial sliding portion; 63: a first adjustment pin; 64, a first adjustment aperture; 65: a first adjusting bolt; 7: a second side mold; 71: a second axial sliding part; 72: a second radial sliding portion; 73: a second adjustment pin; 74, a second adjusting hole; 75: a first adjusting bolt;
8: a theoretical outer profile of the cabin section; 8': an actual outer profile of the cabin section;
9: a thermal protection layer; 91: a theoretical inner profile of the thermal shield; 92: a theoretical outer profile of the thermal protection layer; 91': an actual inner profile of the thermal shield; 92': an actual outer profile of the thermal shield;
10: a theoretical maximum outer profile of the thermal protection layer;
100: a first interference region; 200: a second interference region.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
In the description of the present invention, it should be noted that the front end of the cabin refers to an end of the aircraft that is located at the front side when the aircraft flies, and the rear end of the cabin refers to an end of the aircraft that is located at the rear side when the aircraft flies.
Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Example one
Referring to fig. 1, the tooling provided by the embodiment of the invention, in which a rigid thermal protection layer is sleeved on a cabin section of a non-closed constant-diameter revolving body, includes a bottom plate 1, four upright posts 2, a front extension portion 3, a rear extension portion 4 and at least one sliding die, wherein one end of each upright post 2 is vertically connected to the bottom plate 1, the front extension portion 3 and the rear extension portion 4 are respectively installed at the front end and the rear end of the cabin section 5, and the axial dimensions of the front end and the rear end of the cabin section 5 are extended, so that the axial allowance of the thermal protection layer is also well installed and fixed, and the quality of the thermal protection layer at the edge of the front end and the edge of the rear end is. The front and rear extensions 3, 4 are generally cylindrical structures of equal diameter to the cabin section.
The sliding die comprises a first side die 6 and a second side die 7, wherein the first side die 6 comprises a first axial sliding part 61 and a first radial sliding part 62, the first axial sliding part 61 is installed on two vertical columns 2 are and can be arranged along two axial movement of the vertical columns, and the first radial sliding part 62 is installed on the first axial sliding part 61 and can be arranged along radial movement of the vertical columns 2. The second side die 7 comprises a second axial sliding portion 71 and a second radial sliding portion 72, the second axial sliding portion 71 is mounted on the other two columns 2 and can move along the axial direction of the columns 2, the second radial sliding portion 72 is mounted on the second axial sliding portion 71 and can move along the radial direction of the columns 2, when the first side die 6 and the second side die 7 are clamped, the first radial sliding portion 62 and the second radial sliding portion 72 are butted to form a containing space for containing the cabin section 5 sleeved with the thermal protection layer, and the inner profile surfaces of the first radial sliding portion 62 and the second radial sliding portion 72 are used for limiting the maximum deviation amount of the thermal protection layer in the radial direction.
In the present embodiment, the first axial sliding portion 61 and the column 2, and the first radial sliding portion 62 and the first axial sliding portion 62 can be slidably connected through a sliding rail structure, or can be connected through a tight fit manner, so that the first axial sliding portion can move when it is needed, and the position after the movement is maintained.
In a specific embodiment, the first axial sliding portion 61 is a block structure, and two first through holes are formed on the first axial sliding portion 61 for penetrating the two columns 2, and a first mounting hole is formed on the first radial sliding portion 62 for penetrating the first radial sliding portion 62, so that the first radial sliding portion 62 and the first axial sliding portion 61 can be slidably connected. The second axial sliding portion 71 is a block-shaped structure, and two second through holes for penetrating the two columns 2 respectively and a second mounting hole for penetrating the second radial sliding portion 72 are formed in the second axial sliding portion 71, so that the second radial sliding portion 72 and the second axial sliding portion 71 can be slidably connected.
The first radial sliding portion 62 and the second radial sliding portion 72 include a connecting portion and a solid portion, the connecting portion is matched with the first mounting hole in shape, one end of the connecting portion is arranged in the first mounting hole in a penetrating mode, the other end of the connecting portion is connected with the solid portion, and the solid portion is of a semicircular structure.
The bottom plate 1 is provided with an annular bulge 11 for accommodating the rear extension part 4, so that the connection between the rear extension part and the bottom plate 1 is realized.
Preferably, a plurality of positioning portions 41 protruding in the radial direction are provided on the circumferential direction of the rear extension portion 4 for circumferentially positioning the thermal protection layer. Specifically, the rear end of the thermal protection layer has a plurality of notches or recesses matched with the positioning portion 41, so that circumferential accurate positioning is achieved.
When the thermal protection device is used, the thermal protection layer is sleeved on the cabin section 5, the front extension part 3 and the rear extension part 4 of the cabin section, the rear end of the thermal protection layer is abutted to the bottom plate 1, the axial positioning of the thermal protection layer is realized, the circumferential positioning of the thermal protection layer is adjusted, the sliding die is adjusted to perform radial limiting, and the thermal protection layer is sleeved on the unclosed equal-diameter revolving body cabin section efficiently and accurately.
The front extension portion 3 and the rear extension portion 4 may be connected to the cabin 5 through a screw hole and/or a pin hole that are provided in the cabin 5, or may be connected to the cabin 5 through a commonly used cover such as an insert connection or a screw connection, and the connection method is not limited to a specific connection method.
It should be noted that the bottom plate 1 may be a single bottom plate, or may be a part of a floor or a table, and is not limited herein.
It is worth mentioning that two side moulds of the sliding mould, each side mould can also be mounted on other number of uprights 2, for example, each side mould is mounted on one upright 2, or can be mounted on three uprights 2.
Example two
Referring to fig. 2 and fig. 3, the second embodiment is substantially the same as the first embodiment, and the description of the same parts is omitted, except that: a plurality of first adjusting holes 64 are formed in at least one column 2 for mounting the first axial sliding portion 61, the plurality of first adjusting holes 64 are arranged at intervals in the axial direction of the column 2, and the first side die 6 is fixed at the upper position in the axial direction of the column 2 by the first adjusting pin 63 matching with the first adjusting holes 64.
A plurality of second adjusting holes 74 are formed in at least one of the columns 2 for mounting the second axial sliding portion 71, the plurality of second adjusting holes 74 are arranged at intervals in the axial direction of the column 2, and the second side die 7 is fixed at a position in the axial direction of the column 2 by a second adjusting pin 73 in cooperation with the second adjusting holes 74.
Preferably, the first axial sliding portion 61 is further provided with a first radial adjusting screw hole perpendicular to the first mounting hole, the first adjusting bolt 65 is matched with the first radial adjusting screw hole, and after the first radial sliding portion is adjusted to a proper position, the first adjusting bolt 65 is screwed to abut against the first radial sliding portion 62, so as to fix the position of the first radial sliding portion 62. The second radial sliding portion 71 is further provided with a first radial adjusting screw hole perpendicular to the first mounting hole, the first adjusting bolt 65 is matched with the first radial adjusting screw hole, and after the first radial sliding portion 62 is adjusted to a proper position, the first adjusting bolt 65 is screwed to abut against the first radial sliding portion 62, so that the position of the first radial sliding portion 62 is fixed.
A second radial adjusting screw hole perpendicular to the second mounting hole is further formed in the second axial sliding portion 71, the second adjusting bolt 75 is matched with the second radial adjusting screw hole, and after the second radial sliding portion 72 is adjusted to a proper position, the second adjusting bolt 75 is screwed to abut against the second radial sliding portion 72 to fix the position of the second radial sliding portion 72.
EXAMPLE III
The third embodiment is an improvement on the basis of any one of the first embodiment and the second embodiment, and the same parts are not described again, except that: including a plurality of sliding die, it is a plurality of sliding die is followed the axial of stand 2 is installed stand 2 through the position adjustment to a plurality of sliding die, realizes the segmentation location of heat protection layer, can avoid interfering the position, has both avoided interfering the damage cabin body, can guarantee the profile tolerance after the heat protection layer cup joints again by the at utmost.
Referring to fig. 4, a tooling structure is shown, which includes two sliding dies, but in other embodiments, the number of the sliding dies may be adjusted as needed, for example, three sliding dies, four sliding dies.
Example four
The embodiment provides a method for sleeving a rigid thermal protection layer on a non-closed constant-diameter revolving body cabin section, wherein any one of the tools in the first embodiment to the third embodiment is used for auxiliary installation, and the method comprises the following steps of:
respectively carrying out three-coordinate scanning on the inner molded surface of the thermal protection layer and the outer molded surface of the cabin section;
step two, comparing the data scanned twice in the step one to obtain the maximum gap amount between the thermal protection layer and the cabin section, and calculating the glue consumption;
thirdly, the front extension part and the rear extension part are respectively arranged at the front end and the rear end of the cabin section, and the cabin section is arranged on the bottom plate through the rear extension part;
gluing the outer molded surface of the cabin section and the inner molded surface of the thermal protection layer;
sleeving the thermal protection layer on the cabin section to perform axial and circumferential positioning;
sixthly, adjusting the position of the sliding die;
and step seven, dismantling the tool after the glue solution is cured.
Preferably, when the data is compared in the second step, the outer profile of the cabin segment is used as a reference, and a clearance cloud map is obtained by three-coordinate data comparison, so as to distinguish a clearance area and an interference area between the thermal protection layer and the cabin segment, for example, a red area is used to indicate that a clearance exists between the thermal protection layer and the cabin segment, a blue area is used to indicate that interference occurs between the thermal protection layer and the cabin segment, the interference area to be avoided is marked, the interference area of the sliding die avoiding mark is adjusted, and the area is prevented from being extruded by the sliding die to damage the thermal protection layer or the cabin after the die assembly is in place.
Preferably, the method for determining the interference area to be marked is as follows: determining whether an interference region satisfies the following relationship a + T > b + T, and marking the interference region if a + T > b + T is satisfied;
wherein a is the actual profile degree of the cabin section of the interference area, T is the actual thickness of the thermal protection layer of the interference area, b is the theoretical maximum positive deviation of the thermal protection layer, and T is the sum of the theoretical thicknesses of the thermal protection layer and the adhesive layer.
In a specific embodiment, with reference to fig. 5, two interference zones are obtained by means of a cloud of clearance, respectively a first interference zone 100 and a second interference zone 200, the theoretical outer profile 8 of the section of the tank, the theoretical inner profile 91 of the thermal protection layer and the theoretical outer profile 92 of the thermal protection layer in fig. 5 are all theoretical dimensions (positions) required by the design, the theoretical maximum outer profile 10 of the thermal protection layer is the maximum outer profile allowed by the design, the difference from the theoretical outer profile 92 of the thermal protection layer is the theoretical maximum positive deviation of the thermal protection layer, and the theoretical maximum outer profile 10 of the thermal protection layer is the position defined by the first radial sliding portion 62.
In actual production, due to reasons such as manufacturing precision, the actual outer profile 8 'of the cabin segment interferes with the inner profile of the thermal protection layer 9, and the corresponding thermal protection layer 9 is deformed to a certain extent, so that the positions of the actual inner profile 91' of the thermal protection layer and the actual outer profile 92 'of the thermal protection layer are changed relative to their theoretical positions, and when the change of the actual outer profile 92' of the thermal protection layer exceeds the theoretical maximum outer profile 10 of the thermal protection layer (see the second interference region 200 in fig. 5), that is, the interference region satisfies a + T > b + T, the interference region is marked, and the sliding mold is to avoid the region. If the actual outer profile 92' of the thermal shield does not change beyond the theoretical maximum outer profile 10 of the thermal shield (see first interference zone 200 in fig. 5), i.e. this interference zone satisfies a + T < b + T, then there is no need to mark this interference zone.
It should be noted that the changes of the theoretical profiles and the actual profiles in fig. 5 are only illustrative and do not coincide with the actual changes, and the division of the first interference region 100 and the second interference region 200 is also for illustrative purposes and is not a limitation of the present application.
Preferably, in the fifth step, the thermal protection layer is sleeved in front of the cabin section, the non-product area (the part of the thermal protection layer corresponding to the non-closed area of the cabin section) of the thermal protection layer is axially cut, when in sleeving, a proper force is applied to slightly break the thermal protection layer in the circumferential direction and then the thermal protection layer is sleeved on the cabin section, and the rear end of the thermal protection layer is dropped on the bottom plate to perform axial positioning.
Preferably, a plurality of radially protruding positioning portions are arranged in the circumferential direction of the rear extension portion, and the thermal protection layer is circumferentially positioned by the positioning portions.
In one embodiment, the minimum glue usage (volume or mass) is calculated by the maximum clearance amount, and preferably, the actual glue usage is larger than the calculated minimum glue usage, so as to avoid the glue layer from shrinking after the glue layer is pressed, and the thickness of the glue layer is too thin, while the actual glue usage is larger than the calculated minimum glue usage, and after the maximum outline is defined, the excessive glue usage can be extruded, and the implementation of the scheme of the application is not influenced. For example, red silicone rubber is commonly used in the thermal protection profession of an aircraft, the density of the red silicone rubber is greater than that of water, and if the minimum rubber consumption is calculated to be 1000g, the actual rubber consumption is preferably 1300 g-1500 g.
The allowance of the thermal protection layer in the circumferential direction and the axial direction is removed by a machine tool machining method after the thermal protection layer and the cabin section are assembled and bonded in place.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: each embodiment does not include only one independent technical solution, and in the case of no conflict between the solutions, the technical features mentioned in the respective embodiments can be combined in any way to form other embodiments which can be understood by those skilled in the art.
Furthermore, modifications may be made to the technical solutions described in the foregoing embodiments, or equivalents may be substituted for some of the technical features thereof, without departing from the scope of the present invention, and the essence of the corresponding technical solutions does not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. The utility model provides a frock in non-closed constant diameter solid of revolution cabin section is cup jointed to rigidity thermal protection layer which characterized in that includes:
a base plate;
the upright posts are provided with a plurality of upright posts, and one ends of the upright posts are vertically connected to the bottom plate;
the front extension part is arranged at the front end of the cabin section and is used for extending the axial length of the front end of the cabin section;
one end of the rear extension part is installed at the rear end of the cabin section, and the other end of the rear extension part is connected with the bottom plate and used for extending the axial length of the rear end of the cabin section; and
at least one sliding die, the sliding die includes first side mould and second side mould, first side mould includes first axial sliding portion and first radial sliding portion, first axial sliding portion installs at least one the stand, and can follow the axial displacement of stand, first radial sliding portion installs first axial sliding portion, and can follow the radial movement of stand, second side mould includes second axial sliding portion and second radial sliding portion, second axial sliding portion installs at least one the stand, and can follow the axial displacement of stand, second radial sliding portion installs second axial sliding portion, and can follow the radial movement of stand, work as first side mould with during the compound die of second side mould, first radial sliding portion with the butt joint of second radial sliding portion forms accommodation space, used for accommodating the cabin section sleeved with the thermal protection layer.
2. The tooling of claim 1, wherein:
the number of the upright posts is four;
the first axial sliding portion is mounted on two of the columns, and the second axial sliding portion is mounted on the other two of the columns.
3. The tooling of claim 1, wherein: the slide mechanism comprises a plurality of slide dies which are mounted on the upright post along the axial direction of the upright post.
4. The tooling of claim 1, wherein: the first axial sliding part is provided with at least one first through hole for penetrating the upright post;
a plurality of first adjusting holes are formed in at least one upright post used for mounting the first axial sliding part, the first adjusting holes are arranged at intervals along the axial direction of the upright post, and the position of the first side die in the axial direction of the upright post is fixed through the matching of a first adjusting pin and the first adjusting holes;
the second axial sliding part is provided with at least one second through hole for penetrating the upright post;
a plurality of second adjusting holes are formed in at least one upright post used for mounting the second axial sliding part, the second adjusting holes are arranged at intervals along the axial direction of the upright post, and the position of the second side die in the axial direction of the upright post is fixed through the matching of a second adjusting pin and the second adjusting holes; and/or
The first axial sliding part is provided with a first mounting hole for mounting the first radial sliding part, the first radial sliding part can slide in the first mounting hole along the radial direction of the upright column, the first axial sliding part is also provided with a first radial adjusting screw hole perpendicular to the first mounting hole, and the first adjusting bolt is matched with the first radial adjusting screw hole and used for fixing the position of the first radial sliding part;
the second axial sliding portion is provided with a second mounting hole used for mounting the second radial sliding portion, the second radial sliding portion can be arranged along the radial direction of the stand column and can slide in the second mounting hole, the second axial sliding portion is further provided with a second radial adjusting screw hole perpendicular to the second mounting hole, and the second adjusting bolt is matched with the second radial adjusting screw hole and used for fixing the position of the second radial sliding portion.
5. The tooling of claim 1, wherein: and a plurality of positioning parts extending along the radial direction are arranged in the circumferential direction of the rear extension part and used for circumferentially positioning the thermal protection layer.
6. A method for sleeving a rigid thermal protection layer on a non-closed constant-diameter revolving body cabin section is characterized in that: use the frock of any one of claims 1-4 for auxiliary installation, comprising the steps of:
respectively carrying out three-coordinate scanning on the inner molded surface of the thermal protection layer and the outer molded surface of the cabin section;
step two, comparing the data scanned twice in the step one to obtain the maximum gap amount between the thermal protection layer and the cabin section, and calculating the glue consumption;
thirdly, the front extension part and the rear extension part are respectively arranged at the front end and the rear end of the cabin section, and the cabin section is arranged on the bottom plate through the rear extension part;
gluing the outer molded surface of the cabin section and the inner molded surface of the thermal protection layer;
sleeving the thermal protection layer on the cabin section to perform axial and circumferential positioning;
sixthly, adjusting the position of the sliding die;
and step seven, dismantling the tool after the glue solution is cured.
7. The method of claim 6, wherein: when the data are compared in the second step, the outer profile contour of the cabin section is used as a reference, a clearance cloud picture is obtained through three-coordinate data comparison, a clearance area and an interference area for the thermal protection layer and the cabin section are distinguished, the interference area needing to be avoided is marked, and the sliding die is adjusted to avoid the marked interference area.
8. The method of claim 7, wherein: if the interference region meets a + T > b + T, marking the interference region;
wherein a is the actual profile of the cabin section of the interference region, T is the actual thickness of the thermal protection layer of the interference region, b is the theoretical maximum positive deviation of the thermal protection layer, and T is the sum of the theoretical thicknesses of the thermal protection layer and the adhesive layer.
9. The method of claim 6, wherein:
in the fifth step, the thermal protection layer is sleeved in front of the cabin section, the non-product area of the thermal protection layer is cut off along the axial direction, and the thermal protection layer is sleeved in the cabin section after being slightly broken off along the circumferential direction by proper force application during sleeving;
and dropping the rear end of the thermal protection layer onto the bottom plate for axial positioning.
10. The method according to claim 6 or 9, characterized in that: the circumference of the rear extension part is provided with a plurality of radial protruding positioning parts, and the thermal protection layer is circumferentially positioned by the positioning parts.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011284783.2A CN112483521B (en) | 2020-11-17 | 2020-11-17 | Tool and method for sleeving rigid thermal protection layer on unclosed equal-diameter revolving body cabin section |
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| CN202011284783.2A CN112483521B (en) | 2020-11-17 | 2020-11-17 | Tool and method for sleeving rigid thermal protection layer on unclosed equal-diameter revolving body cabin section |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114082597A (en) * | 2021-11-19 | 2022-02-25 | 航天特种材料及工艺技术研究所 | Sleeving tool and sleeving method for cabin rigid closed type outer heat-proof layer |
| CN114228170A (en) * | 2021-10-27 | 2022-03-25 | 北京星航机电装备有限公司 | Device and method for bonding protective layer and cabin section of revolving body |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120082808A1 (en) * | 2009-06-15 | 2012-04-05 | Aircelle | Method for installing heat shielding on a fixed internal structure of a jet engine nacelle |
| CN207256600U (en) * | 2017-08-28 | 2018-04-20 | 象山杰尔德智能科技有限公司 | A kind of architectural engineering punching fixed equipment |
| CN108190044A (en) * | 2017-12-05 | 2018-06-22 | 北京星航机电装备有限公司 | A kind of aircraft assembles assembly method of the holoaxial to thermal protection component |
| CN110524915A (en) * | 2019-09-05 | 2019-12-03 | 航天特种材料及工艺技术研究所 | A kind of socket forming frock and socket forming method |
| CN111144046A (en) * | 2019-12-23 | 2020-05-12 | 南京航空航天大学 | Assembly gap determining method based on thin-wall part external mold line control |
-
2020
- 2020-11-17 CN CN202011284783.2A patent/CN112483521B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120082808A1 (en) * | 2009-06-15 | 2012-04-05 | Aircelle | Method for installing heat shielding on a fixed internal structure of a jet engine nacelle |
| CN207256600U (en) * | 2017-08-28 | 2018-04-20 | 象山杰尔德智能科技有限公司 | A kind of architectural engineering punching fixed equipment |
| CN108190044A (en) * | 2017-12-05 | 2018-06-22 | 北京星航机电装备有限公司 | A kind of aircraft assembles assembly method of the holoaxial to thermal protection component |
| CN110524915A (en) * | 2019-09-05 | 2019-12-03 | 航天特种材料及工艺技术研究所 | A kind of socket forming frock and socket forming method |
| CN111144046A (en) * | 2019-12-23 | 2020-05-12 | 南京航空航天大学 | Assembly gap determining method based on thin-wall part external mold line control |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114228170A (en) * | 2021-10-27 | 2022-03-25 | 北京星航机电装备有限公司 | Device and method for bonding protective layer and cabin section of revolving body |
| CN114228170B (en) * | 2021-10-27 | 2023-11-07 | 北京星航机电装备有限公司 | Device and method for bonding protection layers and cabin sections of revolution bodies |
| CN114082597A (en) * | 2021-11-19 | 2022-02-25 | 航天特种材料及工艺技术研究所 | Sleeving tool and sleeving method for cabin rigid closed type outer heat-proof layer |
| CN114082597B (en) * | 2021-11-19 | 2022-07-05 | 航天特种材料及工艺技术研究所 | Sleeving tool and sleeving method for cabin rigid closed type outer heat-proof layer |
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| CN112483521B (en) | 2022-05-31 |
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