CN114789415A - Rudder shaft component assembly tool and assembly method for ceramic-based composite material aircraft - Google Patents
Rudder shaft component assembly tool and assembly method for ceramic-based composite material aircraft Download PDFInfo
- Publication number
- CN114789415A CN114789415A CN202210501700.3A CN202210501700A CN114789415A CN 114789415 A CN114789415 A CN 114789415A CN 202210501700 A CN202210501700 A CN 202210501700A CN 114789415 A CN114789415 A CN 114789415A
- Authority
- CN
- China
- Prior art keywords
- shaft
- rudder shaft
- assembly
- rudder
- plate
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 68
- 239000002131 composite material Substances 0.000 title claims abstract description 19
- 239000000919 ceramic Substances 0.000 title claims abstract description 11
- 238000003825 pressing Methods 0.000 claims abstract description 55
- 239000011153 ceramic matrix composite Substances 0.000 claims abstract description 16
- 239000000463 material Substances 0.000 claims abstract description 6
- 238000001514 detection method Methods 0.000 claims description 18
- 238000003754 machining Methods 0.000 claims description 14
- 238000004026 adhesive bonding Methods 0.000 claims description 13
- 238000000151 deposition Methods 0.000 claims description 12
- 238000000227 grinding Methods 0.000 claims description 12
- 230000008021 deposition Effects 0.000 claims description 11
- 238000012545 processing Methods 0.000 claims description 11
- 239000011159 matrix material Substances 0.000 claims description 9
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 6
- 238000009434 installation Methods 0.000 claims description 6
- 239000000126 substance Substances 0.000 claims description 6
- 238000001764 infiltration Methods 0.000 claims description 4
- 230000008595 infiltration Effects 0.000 claims description 4
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 3
- 229910052786 argon Inorganic materials 0.000 claims description 3
- 239000001257 hydrogen Substances 0.000 claims description 3
- 229910052739 hydrogen Inorganic materials 0.000 claims description 3
- 238000007781 pre-processing Methods 0.000 claims description 3
- 239000012495 reaction gas Substances 0.000 claims description 3
- DWAWYEUJUWLESO-UHFFFAOYSA-N trichloromethylsilane Chemical compound [SiH3]C(Cl)(Cl)Cl DWAWYEUJUWLESO-UHFFFAOYSA-N 0.000 claims description 3
- 238000009966 trimming Methods 0.000 claims description 3
- 238000007514 turning Methods 0.000 claims description 3
- 150000001875 compounds Chemical class 0.000 claims 1
- 238000002360 preparation method Methods 0.000 abstract description 7
- 238000010586 diagram Methods 0.000 description 7
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 7
- 229910010271 silicon carbide Inorganic materials 0.000 description 7
- 239000004744 fabric Substances 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 4
- 238000000465 moulding Methods 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 230000000712 assembly Effects 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 230000006378 damage Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 210000005069 ears Anatomy 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 238000010030 laminating Methods 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 238000012356 Product development Methods 0.000 description 1
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003575 carbonaceous material Substances 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 238000005137 deposition process Methods 0.000 description 1
- 238000001035 drying Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 238000004506 ultrasonic cleaning Methods 0.000 description 1
- 238000009941 weaving Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
- B25B11/02—Assembly jigs
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Connection Of Plates (AREA)
Abstract
The invention relates to a rudder shaft type component assembling tool, in particular to a rudder shaft type component assembling tool and an assembling method for a ceramic matrix composite material aircraft. The technical problems of complex assembly process, poor assembly precision and quality, high requirement on single part preparation and high cost of the existing ceramic-based composite material rudder shaft type component are solved. The assembly tool comprises a shaft positioning component and a framework assembly positioning component; the shaft positioning component comprises a bottom plate, a V-shaped seat and a shaft pressing plate, wherein the V-shaped seat and the shaft pressing plate are arranged on the bottom plate; the shaft pressing plate is connected with the V-shaped seat to form a triangular frame structure for fixing the limiting rudder shaft; the framework assembling and positioning assembly comprises a supporting seat and a framework limiting block which are arranged on the bottom plate; the supporting seat and the framework limiting block are respectively provided with a first waist-shaped hole and a second waist-shaped hole, and the first waist-shaped hole and the second waist-shaped hole correspond to pin holes in two sides of the rudder shaft member connecting beam respectively and are used for positioning the framework assembly. The invention also provides a method for assembling rudder shaft members by using the tool.
Description
Technical Field
The invention relates to a rudder shaft type component assembling tool, in particular to a rudder shaft type component assembling tool and a rudder shaft type component assembling method for a ceramic matrix composite aircraft, which are mainly applied to the field of thermal protection of composite aircraft structures with high strength, oxidation resistance and high temperature resistance.
Background
The ceramic matrix composite has the advantages of metal material, ceramic material and carbon material, is a novel strategic material with integrated thermal structure and function, has the characteristics of high temperature resistance, low density, high specific strength, high specific modulus, oxidation resistance, ablation resistance, insensitivity to crack, no catastrophic damage and the like, and is widely applied to the fields of aviation, aerospace, satellite space navigation, nuclear energy, photovoltaic and the like.
Because the prior composite material weaving and forming process technology is limited and is difficult to realize the integral preparation of large-size and precise complex product components, in order to shorten the product development period and improve the product quality, the method of firstly preparing small-size parts and then adopting an online integrated assembly method is mostly adopted.
The existing assembly method for shaft-type components such as rudders, wings and the like of common ceramic-based composite material aircrafts mostly adopts 'horizontal-lying type' assembly, namely an assembly method that a shaft is parallel to a basic table top of an assembly tool. The shaft member is exemplified by, but not limited to, a rudder shaft type product shown in fig. 1, and as shown in fig. 1, a rudder and wing type with shaft type member of an aircraft generally consists of a rudder shaft, a skeleton assembly, a side beam assembly, a lug assembly and a skin. The side beam assembly and the lug assembly are respectively arranged at two ends of the rudder shaft. The framework assembly consists of a shaft sleeve, a connecting beam, a shaft base plate, a front connecting arc plate and a rear connecting arc plate; the side beam assembly consists of an upper side beam and a lower side beam; the ear panel assembly consists of two upper ears and two lower ears.
In a common 'horizontal type' assembly method, a tool and a limiting device need to be repeatedly disassembled and clamped during assembly, and the operation process is complicated; the requirement on the part preparation precision is high, and the part preparation cost is high; when the framework parts are assembled, the narrow space at one side close to the tool table surface is easy to cause, so that the repairing and assembling operation is difficult, and the size of the composite material product component at one side far away from the tool table surface is seriously out of tolerance; in order to meet the requirements of 'flat-lying type' assembly of the whole component product, the requirements of the size of an assembly table top are large, the manufacturing precision and the cost are high, and the like. Therefore, the requirements of various performance indexes of the thermal protection product of the aircraft cannot be met, and certain measures and new methods are needed to improve the assembly quality of the ceramic matrix composite aircraft component product, particularly the assembly quality of the rudder shaft component.
Disclosure of Invention
The invention aims to solve the technical problems that the assembly process is complicated, the assembly precision is low, the requirement on the preparation precision of a single part is high, the assembly cost is high, the split surface of a composite material framework is not coplanar with the axis of a steering shaft, and the like in the conventional assembly method of shaft-type components such as rudders, wings and the like of ceramic matrix composite aircrafts, and the requirements of various performance indexes of thermal protection products of aircrafts are difficult to meet, and provides an assembly tool and an assembly method of the steering shaft-type components for the ceramic matrix composite aircrafts.
The technical solution of the invention is as follows:
the utility model provides a ceramic matrix is rudder axle class component assembly fixture for combined material aircraft which the special character lies in: the device comprises a shaft positioning component and a framework assembling and positioning component;
the shaft positioning assembly comprises a bottom plate, a V-shaped seat and a shaft pressing plate;
the bottom plate is sequentially provided with a V-shaped groove, a first rectangular groove and a second rectangular groove along the length direction, and the small end of the V-shaped groove is in contact with the first rectangular groove; the V-shaped seat is fixedly arranged in the V-shaped groove, and the height of the V-shaped seat is matched with the length of the rudder shaft;
the shaft pressing plate is matched with the large end of the V-shaped seat, the shaft pressing plate is fixedly connected with the large end of the V-shaped seat to form a triangular frame structure, and three inner side surfaces of the triangular frame structure are in tangential contact with the outer surface of the rudder shaft;
the framework assembling and positioning assembly comprises a supporting seat, a framework limiting block and two positioning pins;
the supporting seat is fixedly arranged in the first rectangular groove; the upper end surface of the supporting seat, the upper end surface of the V-shaped seat and the upper end surface of the shaft pressing plate are all positioned on the same horizontal plane; the upper end face of the supporting seat is provided with a first waist-shaped hole;
the framework limiting block is a Z-shaped knot with a right-angled corner, and the bottom end of the framework limiting block is fixedly connected in the second rectangular groove; the inner side of the lower part of the framework limiting block is in contact with one side of the supporting seat; the upper end face of the framework limiting block is parallel to the upper end face of the supporting seat, and the upper end of the framework limiting block is positioned right above the supporting seat; the upper end face of the framework limiting block is used for being matched with the inner side face of the connecting beam of the rudder shaft member, and a gap of 0.3-0.5 mm is formed between the upper end face of the framework limiting block and the inner side face of the connecting beam; the upper end face of the framework limiting block is provided with a second waist-shaped hole, one positioning pin is used for connecting the pin hole on one side of the beam with the second waist-shaped hole, and the other positioning pin is used for connecting the pin hole on the other side of the beam with the first waist-shaped hole.
Furthermore, the device also comprises an auxiliary limiting component; the auxiliary limiting assembly comprises a clamping plate, a fixed rod, a pressing piece, a detection cushion block and a horizontal limiting cushion block; the bottom end of the fixed rod is fixedly connected to the bottom plate and is positioned in the center of the triangular frame structure; the pressing piece is sleeved on the fixed rod and is used for pressing the upper end face of the rudder shaft; the detection cushion block and the clamping plate are matched for use and used for checking the profile of the rudder shaft member in the assembly process; the horizontal limiting cushion block is used for being sleeved on the periphery of the rudder shaft and is positioned between the V-shaped seat and the shaft sleeve and between the supporting seat and the connecting beam.
Further, the thickness of the horizontal limiting cushion block is consistent with the total thickness of the two lower lugs and the lower side beam; the clamping plate is provided with a plurality of lightening holes.
Further, the fixing rod is a double-end screw, and the pressing piece comprises an end cover and a nut; the end cover and the nut are sequentially sleeved on the double-end screw, and the end cover is tightly pressed on the upper end face of the rudder shaft by screwing the nut.
Furthermore, the connection of the V-shaped seat and the shaft pressing plate, the connection of the supporting seat, the framework limiting block and the V-shaped seat and the bottom plate, and the connection of the clamping plate connecting end and the framework limiting block are all in screw connection; the first kidney-shaped hole, the second kidney-shaped hole and all the bolt connection hole positions are provided with 90-degree taper holes, and the depth of each taper hole is 2-3 mm; the shapes of two corners at the upper end of the shaft pressing plate are chamfers.
The method for assembling the rudder shaft type components for the ceramic-based composite material aircraft is characterized by comprising the following steps of:
1) preprocessing each part of the rudder shaft member to ensure that the appearance of each part is clean and the size of each part reaches the standard;
2) the rudder shaft is positioned and installed to ensure that the rudder shaft is stable and vertical to the bottom plate;
3) fix a position the installation with axle sleeve, tie-beam, glued fixed rudder axle, axle sleeve and tie-beam:
4) positioning and mounting the shaft backing plate, processing the outer molded surface of the shaft backing plate and grinding and finishing the shaft backing plate;
5) positioning and mounting the front connecting arc plate and the rear connecting arc plate;
5.1) taking the outer molded surface of the shaft backing plate, the upper end surface of the V-shaped seat and the upper end surface of the shaft pressing plate as references, installing and positioning the front connecting arc plate and the rear connecting arc plate, and ensuring that the front connecting arc plate and the rear connecting arc plate are respectively attached to the outer molded surface of the shaft backing plate, the upper end surface of the V-shaped seat and the contact surface of the upper end surface of the shaft pressing plate;
5.2) gluing the front connecting arc plate and the rear connecting arc plate;
5.3) respectively processing the outer profiles of the front connecting arc plate and the rear connecting arc plate, ensuring that the profile degree is less than or equal to 0.05mm, and grinding and finishing to ensure that the profiles are smooth;
5.4) numerically controlling and processing the upper end surface of the shaft sleeve and the upper side surface of the connecting beam;
6) positioning and mounting the upper side beam;
6.1) positioning and installing an upper side beam by taking the outer molded surface of the rudder shaft, the upper end surface of the shaft sleeve and the upper side surface of the connecting beam as references;
6.2) gluing and fixing the upper side beam;
7) positioning and mounting the two upper lugs;
7.1) sequentially positioning and installing two upper lugs by taking the outer molded surface of the rudder shaft and the upper end surface of the upper side beam as references, and gluing and fixing;
7.2) processing the upper end surface of the upper lug on the outer side, ensuring flatness, reserving a wall thickness allowance of 0.5mm, and ensuring that the planeness is less than or equal to 0.05 mm;
8) positioning and mounting the lower side beam and the lower lug;
taking down the assembly part after 7.2) integrally, turning around and installing the assembly part on a tool, and installing a lower side beam and two lower lugs according to the methods in the steps 6) and 7);
9) mounting a skin by taking the outer profile of the front connecting arc plate, the outer profile of the rear connecting arc plate and the end surface of the outer lug as references, and fixedly connecting the skin with the front connecting arc plate, the rear connecting arc plate, the side beam assembly and the lug assembly integrally to obtain an assembled rudder shaft component;
10) taking the assembled rudder shaft member down from the tool, and carrying out SiC matrix deposition on the appearance of the rudder shaft member;
11) and superfinishing the appearance of the rudder shaft component to obtain the rudder shaft component.
Further, in step 10), deposition of the SiC matrix is carried out by a chemical vapor infiltration process: the deposition time is 30-45 h, the deposition temperature is 850-1000 ℃, and the reaction gas is trichloromethylsilane, argon and hydrogen.
Further, the step 1) specifically comprises: the surfaces of all parts forming the rudder shaft component are polished, polished and cleaned, and then are cleaned and dried, so that the appearances of all parts are ensured to have no redundant substances, and the appearances and the sizes of all parts reach the standard;
the step 2) is specifically as follows: positioning and mounting the rudder shaft on a shaft positioning assembly, and ensuring that the fit clearance between the outer profile of the rudder shaft and three inner side surfaces of the triangular frame structure is less than or equal to 0.05mm and the verticality between the axis of the rudder shaft and the bottom plate is less than or equal to 0.05/500 mm;
the step 3) is specifically as follows:
3.1) mounting the shaft sleeve on the steering shaft, ensuring that the fit clearance between the inner arc surface of the shaft sleeve and the outer surface of the steering shaft is less than or equal to 0.05mm, and ensuring that the lower end surface of the shaft sleeve is firmly attached to the upper end surface of the V-shaped seat and the upper end surface of the shaft pressing plate;
3.2) tightly attaching the outer side surface of one side of the connecting beam with the upper end surface of the V-shaped seat and the upper end surface of the supporting seat, adjusting the positions of the shaft sleeve and the connecting beam, and ensuring that the connecting beam is attached to the molded surface of the shaft sleeve; respectively aligning pin holes on two sides of the connecting beam with a second waist-shaped hole on the framework limiting block and a first waist-shaped hole on the supporting seat, and gluing and fixing the rudder shaft, the shaft sleeve and the connecting beam;
the step 4) is specifically as follows:
4.1) installing a shaft backing plate by taking the fixed shaft sleeve and the fixed connecting beam as a reference to ensure that the fit clearance between the inner molded surface of the shaft backing plate and the outer molded surface of the shaft sleeve is less than or equal to 0.05 mm;
4.2) machining the outer profile of the shaft backing plate by adopting numerical control, and ensuring that the profile degree of the outer profile of the shaft backing plate is less than or equal to 0.05 mm; detecting the profile height point, and grinding and finishing to ensure the smooth profile of the shaft gasket;
in the step 5.1), the fit clearance between the inner molded surfaces of the front connecting arc plate and the rear connecting arc plate and the outer molded surface of the shaft backing plate is less than or equal to 0.05 mm;
in the step 5.3), the grinding and fine trimming to ensure that the molded surface is smooth specifically comprises the following steps: detecting the high points of the molded surfaces of the front connecting arc plate and the rear connecting arc plate, and grinding and finishing to ensure the molded surfaces to be smooth;
the step 6.1) is specifically as follows: taking the outer profile of the steering shaft, the upper end surface of the shaft sleeve and the upper side surface of the connecting beam as references, positioning and installing the upper side beam to ensure that the assembly gap between the upper side beam and the outer profile of the steering shaft is less than or equal to 0.1mm, and the fitting gap between the upper side beam and the upper end surface of the shaft sleeve and the upper side surface of the connecting beam is less than or equal to 0.05 mm;
the step 7.1) is specifically as follows: sequentially positioning and mounting two upper lugs by taking the outer profile of the rudder shaft and the upper end surface of the upper side beam as references, ensuring that the joint clearance between the two upper lugs and the profile between the upper lugs and the upper side beam is less than or equal to 0.05mm, and gluing and fixing;
the step 9) is specifically as follows: mounting a skin by taking the outer surface of the front connecting arc plate, the outer surface of the rear connecting arc plate and the end surface of the outer lug as references, ensuring that the joint gaps between the skin and the outer surfaces of the front connecting arc plate and the rear connecting arc plate are less than or equal to 0.1mm, and integrally and fixedly connecting the skin with the front connecting arc plate, the rear connecting arc plate, the side beam assembly and the lug assembly to obtain an assembled rudder shaft component;
the step 11) is specifically as follows: and resetting and mounting the deposited rudder shaft member on a tool, and carrying out numerical control superfinishing on the appearance of the rudder shaft member to ensure the requirement of dimensional precision to obtain the rudder shaft member.
Further, in the step 3.1), horizontal limiting cushion blocks are arranged on the upper end face of the shaft pressing plate, the upper end face of the V-shaped seat and the upper end face of the supporting seat, and the lower end face of the shaft sleeve is tightly attached to the upper end face of the horizontal limiting cushion block;
in the step 3.2), the outer side surface of one side of the connecting beam is tightly attached to the upper end surface of the horizontal limiting cushion block;
in the step 5.1), the mounting references are the processed outer profile of the shaft backing plate and the upper end surface of the horizontal limiting cushion block; the lower end surfaces of the outer convex parts of the front connecting arc plate and the rear connecting arc plate are tightly attached to the upper end surface of the horizontal limiting cushion block;
in the step 8), after the assembly part integral and the horizontal limiting cushion block finished in the step 7.2) are taken down, the assembly part integral is turned around and installed on a tool, and the lower side beam and the two lower lugs are installed according to the methods in the step 6) and the step 7);
in the step 4.2), the profile height point is detected according to the matching use of the detection cushion block and the clamping plate.
Further, the step 2) specifically comprises: the fixing rod is installed on the bottom plate and is located in the center of the triangular frame structure, the rudder shaft is sleeved on the periphery of the fixing rod and is installed on the bottom plate, the fit clearance between the outer profile of the rudder shaft and three inner side surfaces of the triangular frame structure is less than or equal to 0.05mm, the perpendicularity between the axis of the rudder shaft and the bottom plate is less than or equal to 0.05/500mm, and finally the pressing piece is sleeved on the upper end of the rudder shaft from the upper end of the fixing rod and is pressed on the upper end of the rudder shaft.
The invention has the beneficial effects that:
1. the assembly tool disclosed by the invention is simple in structure, simple in assembly operation, high in assembly precision, strong in reliability and low in cost.
2. The assembly method takes the appearance of the steering shaft after finish machining as an assembly reference, the steering shaft is positioned and fixed on the shaft positioning component, and the shaft part is ensured to be vertical to the profile of the tool platform.
3. The assembly method of the invention takes the rudder shaft as the assembly reference of subsequent parts, and ensures that the design reference, the assembly reference and the interface use reference are uniform.
4. The assembly method adopts the tool to ensure the position degree of the rudder shaft and the framework part, and considers the assembly operation realizability and the machinability; the assembly method takes the rudder shaft as an assembly standard, the frame parts are positioned by the aid of the tool, the assembly error is integrally coordinated, the milling processing is carried out in the assembly process, the artificial repair error is avoided, the assembly precision of the parts is improved, and the assembly realizability and the appearance machinability of the shaft and the frame parts are considered.
5. The ceramic matrix composite part assembled by the assembly tool is prepared by laminating silicon carbide or carbon cloth, and in the superfinishing process after assembly, the removal amount can be finely adjusted according to the overall trial machining condition of the appearance, the fault risk of the appearance cloth layer machining is reduced, and the influence on the product strength is reduced.
6. According to the assembling method, the machining integral tool is adopted after final assembly, the fitting precision of the parts is guaranteed, the requirement on the preparation precision of a single part before assembly is low, and the production progress can be greatly improved.
7. The assembling method has the advantages of simple assembling process, high assembling precision, low requirement on the preparation precision of a single part and low assembling cost.
Drawings
FIG. 1 is a schematic structural view of a rudder shaft member;
FIG. 2 is an exploded view of the rudder shaft member;
FIG. 3 is a schematic view of a rudder shaft structure of the rudder shaft member;
FIG. 4 is a structural diagram of a skeleton assembly of a rudder shaft member;
FIG. 5 is an exploded view of the frame assembly in the rudder shaft member;
FIG. 6 is a schematic structural diagram of an embodiment of the assembly fixture of the present invention;
FIG. 7 is a rudder shaft positioning assembly drawing in an embodiment of the assembly method of the present invention;
FIG. 8 is a diagram illustrating the process of assembling the axle sleeves and the connecting beams of the frame assembly according to the embodiment of the assembling method of the present invention;
FIG. 9 is a diagram of an assembly process for a shaft spacer of a skeletal assembly in accordance with an embodiment of the assembly method of the present invention;
FIG. 10 is a schematic view of a test pad profile used with a chuck plate and a test pad in accordance with an embodiment of the assembly method of the present invention;
FIG. 11 is a front and rear attachment arc plate assembly process diagram of a frame assembly in an embodiment of the assembly method of the present invention;
FIG. 12 is a schematic view of a clamping plate and a detecting cushion block used together to detect a front connecting arc plate and a rear connecting arc plate in an embodiment of the assembling method of the present invention;
FIG. 13 is a schematic view showing the assembly of a side sill assembly in an embodiment of the assembly method of the present invention;
FIG. 14 is a schematic view of the assembly of the tab assembly in an embodiment of the assembly method of the present invention;
FIG. 15 is a diagram of a skin assembly process in an embodiment of the assembly method of the present invention;
FIG. 16 is a schematic view of the skin assembly completion in an embodiment of the assembly method of the present invention;
FIG. 17 is a schematic diagram of the integrated coordinated superfinishing of the rudder shaft member in an embodiment of the assembly method of the present invention.
Reference numerals:
1-rudder shaft member, 10-rudder shaft, 11-skeleton assembly, 110-shaft sleeve, 111-connecting beam, 112-shaft backing plate, 113-front connecting arc plate, 114-rear connecting arc plate, 12-side beam assembly, 120-upper side beam, 121-lower side beam, 13-lug assembly, 130-upper lug, 131-lower lug and 14-skin;
20-shaft positioning component, 200-bottom plate, 201-V-shaped seat, 202-shaft pressing plate, 21-framework assembling positioning component, 211-supporting seat, 212-framework limiting block, 213-clamping plate, 221-positioning pin, 222-fixing rod, 223-pressing part, 224-detection cushion block and 225-horizontal limiting cushion block.
Detailed Description
The invention is further described with reference to the following figures and specific embodiments.
Referring to fig. 1 to 5, which are views of a structure of a rudder shaft member 1 to be assembled according to an embodiment of the present invention, the rudder shaft member 1 mainly comprises a rudder shaft 10, a frame assembly 11, a side sill assembly 12, a tab assembly 13, and a skin 14. The side beam assembly 12 and the lug assembly 13 are respectively installed at both ends of the rudder shaft 10. The framework assembly 11 is composed of a shaft sleeve 110, a connecting beam 111, a shaft pad plate 112, a front connecting arc plate and a rear connecting arc plate 113; the side sill assembly 12 is composed of an upper side sill 120 and a lower side sill 121; the ear panel assembly 13 is composed of two upper ear panels 130 and two lower ear panels 131.
As shown in fig. 6 to 17, the assembly fixture for the rudder shaft component for the ceramic matrix composite aircraft comprises a shaft positioning component 20, a framework assembly positioning component 21 and an auxiliary limiting component. The shaft positioning component 20 is used for positioning and fixing the rudder shaft, so that the outer surface of the rudder shaft 10 is fixed, the molded surfaces of the rudder shaft 10 and the shaft positioning component 20 are well fitted, and the shaft parts are perpendicular to the bottom plate 200 platform.
The shaft positioning assembly 20 includes a base plate 200, a V-shaped seat 201, and a shaft pressing plate 202. A V-shaped groove, a first rectangular groove and a second rectangular groove are sequentially arranged on the bottom plate 200 along the length direction, the V-shaped groove is positioned in the middle of the bottom plate 200, and the small end of the V-shaped groove is in contact with the first rectangular groove; the V-shaped seat 201 is fixedly arranged in the V-shaped groove, and the height of the V-shaped seat 201 is matched with the length of the rudder shaft 10, so that the rudder shaft 10 is ensured to be stably installed; the shaft pressing plate 202 is matched with the large end of the V-shaped seat 201, the shaft pressing plate 202 is fixedly connected with the large end of the V-shaped seat 201 to form a triangular frame structure, and three inner side surfaces of the triangular frame structure are matched with and in tangential contact with the outer profile of the rudder shaft 10; the two corners of the upper end of the shaft pressing plate 202 are provided with chamfer angles. The structure of the V-shaped seat 201 and the shaft pressure plate 202 can be disassembled according to the size and the profile complexity of the rudder shaft 10, and the parts are positioned and connected by using pins and bolts. 90-degree taper holes are machined in the hole opening parts of all pin holes or screwed holes in the V-shaped seat 201, the shaft pressing plate 202 and the bottom plate 200, the depth of each taper hole is 2-3 mm, and the standard connecting piece can be conveniently guided into, positioned and installed fast in the tool using or assembling process. The assembly position of the bottom plate 200 and the V-shaped seat 201 is provided with a guiding and positioning V-shaped groove for rapidly positioning the V-shaped seat 201, and the tightness degree of the installation gap between the shaft pressure plate 202 and the V-shaped seat 201 can be adjusted through a connecting bolt in order to adapt to the fitting of the profiles of the rudder shafts 10 of different batches and the tool. The shaft positioning assembly 20 of the present invention includes, but is not limited to, the V-shaped seat 201 and the shaft pressing plate 202 structure, and a three-jaw device with self-centering function may also be used. In order to improve the installation efficiency of the shaft pressing plate 202 and the V-shaped seat 201, the appearance of the shaft pressing plate 202 is designed to be fool-proof, namely, the appearance of one end, far away from the bottom plate 200, of the shaft pressing plate 202 is subjected to chamfering treatment, but not limited to chamfering or oblique angle, and meanwhile, the sharp edge of the tool in the operation process is also prevented from causing injury to personnel.
The framework assembling and positioning assembly 21 comprises a supporting seat 211, a framework limiting block 212 and two positioning pins 221; the supporting seat 211 is fixedly arranged in the first rectangular groove; the upper end surface of the supporting seat 211, the upper end surface of the V-shaped seat 201 and the upper end surface of the shaft pressing plate 202 are all positioned on the same horizontal plane; a first waist-shaped hole is formed in the upper end face of the supporting seat 211; the bottom end of the framework limiting block 212 is fixedly connected in the second rectangular groove; the framework limiting block 212 is of a Z-shaped structure with right-angled corners; the inner side of the lower part of the framework limiting block 212 is contacted with one side of the supporting seat 211; the upper end face of the framework limiting block 212 is parallel to the upper end face of the supporting seat 211, and the upper end of the framework limiting block 212 is positioned right above the supporting seat 211; the upper end face of the framework limiting block 212 is matched with the inner side face of the connecting beam 111 of the rudder shaft member 1, and a gap of 0.3-0.5 mm is formed between the upper end face of the framework limiting block 212 and the inner side face of the connecting beam 111; the upper end face of the framework limiting block 212 is provided with a second waist-shaped hole, during assembly, one positioning pin 221 penetrates through the pin hole and the second waist-shaped hole on one side of the connecting beam 111 in sequence, and the other positioning pin 221 penetrates through the pin hole on the other side of the first waist-shaped hole and the connecting beam 111 in sequence. The first waist-shaped hole and the second waist-shaped hole are used for fixing the framework component 11 and positioning the angular assembly positioning of the (framework part) rudder shaft 10, the shaft sleeve 110, the connecting beam 111, the side beam component 12 and the lug component 13, and the waist-shaped holes are parallel to the bisection plane of the rudder shaft component 1 along the length direction and are used for positioning the assembly angular direction of the framework component 11 and the rudder shaft 10. The shape and contour of the support seat 211 are matched with those of the skeleton assembly 11, and the support seat is used for assisting in positioning the assembly angular direction of the skeleton assembly 11 and the rudder shaft 10; the center positions of the waist-shaped holes on the framework limiting block 212 and the supporting seat 211 are designed according to the structure of a rudder shaft component product.
The auxiliary limiting assembly comprises a clamping plate 213, a fixing rod 222, a pressing piece 223, a detection cushion block 224 and a horizontal limiting cushion block 225; the fixing rod 222 is coaxially arranged with the rudder shaft 10, and the bottom end of the fixing rod 222 is fixedly connected to the bottom plate 200 and is located at the center of the triangular frame structure and the rudder shaft 10 for assisting in fixing and limiting the rudder shaft 10 and the skeleton assembly 11; the pressing piece 223 is sleeved on the fixing rod 222 and pressed on the upper end surface of the rudder shaft 10; the detection cushion block 224 is matched with the clamping plate 213 for use, and is used for checking the profile of the rudder shaft member 1 in the assembling process; the horizontal limit cushion block 225 is located between the V-shaped seat 201 and the support seat 211 and between the shaft sleeve 110 and the connecting beam 111, and is sleeved on the periphery of the rudder shaft 10, and the thickness of the horizontal limit cushion block 225 is consistent with the total thickness of the two lower lugs 131 and the lower side beam 121. Be provided with a plurality of lightening holes on the cardboard 213, be used for lightening cardboard 213 weight on the one hand, on the other hand can be convenient for observe the clearance between measurement cardboard 213 and the relevant part profile. In this embodiment, the fixing rod 222 is a double-threaded screw, and the pressing member 223 is an end cap and a nut; the end cover and the nut are sequentially sleeved on the double-end screw, and the end cover is tightly pressed on the upper end face of the rudder shaft 10 by screwing the nut.
In the embodiment, the detection cushion block 224 can be designed with various thickness specifications according to the actual situation of a product to be assembled, so that the detection control of the gap between the clamping plate 213 and the composite material under different assembly degrees is met, the appearance of the end cover is smaller than the outer diameter of the rudder shaft 10 by 2-3 mm, the center of the end cover is provided with a bolt through hole for being matched with the double-headed screw and the nut 222 to tightly press the end face of the rudder shaft 10, and the overall coordination and finish machining of the appearance size after the assembly is completed is facilitated. The auxiliary limiting assembly is used for fixing and pressing the rudder shaft 10 and the framework assembly 11, the position degree of the rudder shaft 10 and the framework assembly 11 is guaranteed, and sliding does not occur in the assembling and machining processes. The detection pad 224 and the catch plate 213 serve as an assembly process check tool for checking the profile of the component.
The V-shaped seat 201 is connected with the shaft pressing plate 202, the supporting seat 211, the framework limiting block 212 and the V-shaped seat 201 are connected with the bottom plate 200, and the connecting end of the clamping plate 213 is connected with the framework limiting block 212 and is connected with a screw; the first waist-shaped hole, the second waist-shaped hole and all the bolt connection hole positions are provided with 90-degree taper holes, and the depth of each taper hole is 2-3 mm. The rudder shaft member 1 can be turned around to process the hole position on the other side after the hole position on one side of the product is processed by the step pin in the process.
In this embodiment, rudder shaft products such as the rudder shaft 10, the frame component 11, the side beam component 12 and the tab component 13 are used as examples, so that after the integral installation of the rudder shaft 10, the frame component 11, the side beam component 12 and the tab component 13 is completed, the accurate spatial position degree of the rudder shaft 10, the frame component 11, the side beam component 12 and the tab component 13 is maintained, but the rudder shaft is not limited to a cylindrical shaft, and the shape and the fixing position of the rudder shaft can be designed according to the spatial position structures of interfaces of different rudder shaft products.
The invention also provides a method for assembling the rudder shaft type component by using the assembly fixture for the rudder shaft type component for the ceramic-based composite material aircraft, which comprises the following steps of:
1) preprocessing parts of a rudder shaft component 1;
the surfaces of all parts (framework components, namely skins 14, lug assemblies 13, connecting beams 111, shaft backing plates 112, 110-shaft sleeves, side beam assemblies 12, front and rear connecting arc plate parts and the like, and a rudder shaft 10) forming the rudder shaft member 1 are polished, polished and cleaned, ultrasonic cleaning and drying are carried out, and the appearance of all composite material parts is ensured to be free of redundant residues, and the appearance and the size of the parts reach the standard;
2) positioning and mounting the rudder shaft 10;
as shown in fig. 7, the outer profile (service profile) of the rudder shaft 10 after finish machining is taken as the assembly master standard, the rudder shaft 10 is fixed on the shaft positioning assembly 20, and the three lines of positioning and pressing of the rudder shaft 10 are performed by using the V-shaped seat 201 and the shaft pressing plate 202, so that the fit clearance between the outer profile of the rudder shaft 10 and the three inner sides of the triangular frame structure is less than or equal to 0.05mm, and the perpendicularity between the axis of the rudder shaft 10 and the bottom plate 200 is less than or equal to 0.05/500 mm;
compared with the traditional ceramic matrix composite rudder shaft products which mostly adopt a 'horizontal-lying type' assembly method that the rudder shaft is parallel to the tool bottom plate, the invention has the advantages that:
a) the assembly reference is unified with the design reference and the use reference, so that the tolerance is better coordinated and distributed, the phenomenon that the tolerance of the molded surface of the framework part is accumulated on the exposed side when the framework part is assembled in a flat-lying manner is avoided, and the assembly error is reduced; b) the periphery of the shaft part is wide-range open, so that the assembly operation is convenient; c) the ceramic matrix composite part is prepared by laminating silicon carbide or carbon cloth, and in the superfinishing process after assembly, the removal amount can be finely adjusted according to the overall trial machining condition of the appearance, so that the fault risk of the appearance cloth layer machining is reduced, and the influence on the product strength is reduced.
The rudder shaft positioning mode is not limited to positioning of the V-shaped seat 201 and the shaft pressing plate 202, and can also be performed by adopting a self-centering three-jaw device.
3) The shaft sleeve 110 and the connecting beam 111 are positioned and installed as shown in fig. 8:
3.1) placing a horizontal limiting cushion block 225 on the upper end faces of the V-shaped seat 201 and the supporting seat 211 for compensating the thickness space of the two unassembled lower lug plates 131 and the lower side beam 121; the thickness of the horizontal limiting cushion block 225 is consistent with the total wall thickness of the two lower lugs 131 and the lower side beam 121, and the appearance of the horizontal limiting cushion block 225 can be designed according to the actual product;
the shaft sleeve 110 is arranged on the rudder shaft 10, so that the fit clearance between the inner arc surface of the shaft sleeve 110 and the outer surface of the rudder shaft 10 is less than or equal to 0.05mm, and the lower end surface of the shaft sleeve 110 is tightly attached to the upper end surface of the horizontal limiting cushion block 225;
3.2) tightly attaching the outer side surface of one side of the connecting beam 111 to the upper end surface of the horizontal limiting cushion block 225, adjusting the positions of the shaft sleeve 110 and the connecting beam 111 around the axis of the composite rudder shaft 10, and ensuring that the molded surfaces of the connecting beam 111 and the shaft sleeve 110 are attached; respectively aligning pin holes on two sides of the connecting beam 111 with a second waist-shaped hole on the framework limiting block 212 and a first waist-shaped hole on the supporting seat 211, and gluing and fixing the rudder shaft 10, the shaft sleeve 110 and the connecting beam 111;
4) positioning and mounting of the shaft backing plate 112:
4.1) as shown in fig. 9, installing a shaft backing plate 112 by taking the fixed shaft sleeve 110 and the connecting beam 111 as references, ensuring that the joint gap between the inner profile of the shaft backing plate 112 and the outer profile of the shaft sleeve 110 is less than or equal to 0.05mm, riveting the shaft backing plate 112 with the shaft sleeve 110 and the composite rudder shaft 10 by using a technical composite material pin, and then machining the outer profile of the shaft backing plate 112 by adopting numerical control to ensure that the profile tolerance of the outer profile of the shaft backing plate 112 is less than or equal to 0.05mm as a reference for assembling other subsequent parts, thereby eliminating the accumulation of multilayer assembly tolerance;
4.2) as shown in FIG. 10, detecting the high point of the profile of the shaft backing plate 112 according to the clamping plate 213 and the profile detection cushion block 224, and grinding and finishing to ensure the smooth profile of the composite material;
5) the front connecting arc plate 113 and the rear connecting arc plate 114 are positioned and installed;
5.1) as shown in FIG. 11, according to the processed outer profile of the shaft backing plate 112 and the upper end surface of the horizontal limit cushion block 225 as installation reference, installing and positioning the front connecting arc plate 113 and the rear connecting arc plate 114, ensuring that the lower end surfaces of the outer convex parts of the front connecting arc plate 113 and the rear connecting arc plate 114 are tightly attached to the upper end surface of the horizontal limit cushion block 225, and ensuring that the attaching clearance between the inner profile of the front connecting arc plate 113 and the rear connecting arc plate 114 and the outer profile of the shaft backing plate 112 is less than or equal to 0.05 mm;
5.2) gluing the front connecting arc plate 113 and the rear connecting arc plate 114;
as shown in fig. 12, according to the snap gauge 213 and the profile detection cushion 224, the profile high points of the front connecting arc plate 113 and the rear connecting arc plate 114 are detected, and the detection cushion 224 has even detection gaps on the symmetrical surfaces of the front connecting arc plate 113 and the rear connecting arc plate 114, so as to ensure that the fibers are continuous and the fiber cloth does not have a fault when the profile of the connecting arc plate 113/114 is processed by online numerical control;
5.3) carrying out numerical control machining on the outer profiles of the front connecting arc plate 113 and the rear connecting arc plate 114 to ensure that the profile tolerance of the outer profiles of the front connecting arc plate 113 and the rear connecting arc plate 114 is less than or equal to 0.05mm and the profile tolerance is used as the assembly reference of the subsequent skin 14; according to the molding surface high points of the front connecting arc plate 113 and the rear connecting arc plate 114 detected by the clamping plate 213 and the molding surface detection cushion block 224, the molding surface is ensured to be smooth by grinding and fine trimming;
5.4) numerically processing the upper end surface of the shaft sleeve 110 and the upper side surface of the connecting beam 111 to be used as an assembly reference of the upper side beam 120;
6) positioning and mounting the upper side beam 120;
6.1) as shown in FIG. 13, with the outer profile of the rudder shaft 10, the upper end surface of the shaft sleeve 110 and the upper side surface of the connecting beam 111 as references, positioning and installing the upper side beam 120 to ensure that the assembly gap between the upper side beam 120 and the outer profile of the rudder shaft 10 is less than or equal to 0.1mm, and the fitting gap between the upper side beam 120 and the upper end surface of the shaft sleeve 110 and the upper side surface of the connecting beam 111 is less than or equal to 0.05 mm;
6.2) gluing and fixing the upper side beam 120;
7) positioning and mounting of the two upper tabs 130;
7.1) as shown in fig. 14, sequentially positioning and installing two upper lugs 130 by taking the outer profile of the rudder shaft 10 and the upper end surface of the upper side beam 120 as references, ensuring that the fit clearance between the two upper lugs 130 and between the upper lugs 130 and the upper side beam 120 is less than or equal to 0.05mm, and gluing and fixing;
7.2) performing numerical control machining on the upper end face of the upper lug 130 on the outer side, reserving 0.5mm process allowance for the wall thickness of the upper lug 130, and performing contour superfinishing after SiC matrix CVI (chemical vapor infiltration) deposition to ensure that the flatness is less than or equal to 0.05 mm;
8) positioning and mounting the lower side beam 121 and the lower lug 131;
taking down the assembly part finished in the step 7.2) integrally, removing the horizontal limiting cushion block 225, turning around and mounting the assembly part on a tool, and mounting the lower side beam 121 and the two lower lugs 131 according to the methods in the step 6) and the step 7);
9) as shown in fig. 15, the outer surface of the front connecting arc plate 113, the outer surface of the rear connecting arc plate 114, and the end surface of the outer lug are taken as references, the skin 14 is installed, the joint gaps between the skin 14 and the outer surface of the front connecting arc plate 113, the outer surface of the rear connecting arc plate 114, the surface of the side beam assembly 12, and the surface of the lug assembly 13 are all less than or equal to 0.1mm, and the skin 14, the front connecting arc plate 113, the rear connecting arc plate 114, the side beam assembly 12, and the lug assembly 13 are integrally riveted or screwed to obtain an assembled rudder shaft member 1, as shown in fig. 16;
10) taking the assembled rudder shaft member 1 off the tool, and depositing a SiC matrix on the appearance of the rudder shaft member 1 by a chemical vapor infiltration process;
the SiC matrix deposition process comprises the following steps: the deposition time is 30-45 h, the deposition temperature is 850-1000 ℃, and the reaction gas is trichloromethylsilane, argon and hydrogen.
11) Superfinishing;
as shown in fig. 17, the deposited rudder shaft member 1 is reset and mounted on a tool, the stepped pin 221 is matched with the support seat 211 and the waist-shaped hole on the framework limiting block 212 to locate an angular direction through the upper and lower end face process holes of the lug assembly and the appearance of the rudder shaft, the pressing piece 223, the double-thread screw and the nut 222 assist in pressing and fixing, the appearance of the rudder shaft member 1 is numerically controlled and superfinished, the requirement on dimensional accuracy is met, and the rudder shaft member 1 is obtained after finishing processing.
In other embodiments, the horizontal limit pad 225 may not be installed, and the length of the rudder shaft 10 may be designed, and the rudder shaft 10 may be processed after being assembled, so as to ensure the relative position between the rudder shaft 10 and the frame assembly 11. The horizontal limiting cushion block 225 has the advantages that when the upper lug plate 130 and the upper side beam 120 are installed, the thickness space of the two lower lug plates 131 and the lower side beam 121 which are not assembled is compensated, the raw material consumption of the rudder shaft 10 can be better saved, the processing and removing amount of the two ends of the rudder shaft 10 after the assembly is less, the production cost is reduced, and the production efficiency is improved.
Claims (10)
1. The utility model provides a ceramic matrix is rudder shaft class component assembly fixture for compound material aircraft which characterized in that: comprises a shaft positioning component (20) and a framework assembling and positioning component (21);
the shaft positioning assembly (20) comprises a bottom plate (200), a V-shaped seat (201) and a shaft pressing plate (202);
a V-shaped groove, a first rectangular groove and a second rectangular groove are sequentially arranged on the bottom plate (200) along the length direction, and the small end of the V-shaped groove is in contact with the first rectangular groove; the V-shaped seat (201) is fixedly arranged in the V-shaped groove, and the height of the V-shaped seat (201) is matched with the length of the rudder shaft (10);
the shaft pressing plate (202) is matched with the large end of the V-shaped seat (201), the shaft pressing plate (202) is fixedly connected with the large end of the V-shaped seat (201) to form a triangular frame structure, and three inner side surfaces of the triangular frame structure are in tangential contact with the outer profile of the rudder shaft (10);
the framework assembling and positioning assembly (21) comprises a supporting seat (211), a framework limiting block (212) and two positioning pins (221);
the supporting seat (211) is fixedly arranged in the first rectangular groove; the upper end surface of the supporting seat (211), the upper end surface of the V-shaped seat (201) and the upper end surface of the shaft pressing plate (202) are all positioned on the same horizontal plane; a first waist-shaped hole is formed in the upper end face of the supporting seat (211);
the framework limiting block (212) is a Z-shaped knot with a right-angled corner, and the bottom end of the framework limiting block is fixedly connected in the second rectangular groove; the inner side of the lower part of the framework limiting block (212) is in contact with one side of the supporting seat (211); the upper end face of the framework limiting block (212) is parallel to the upper end face of the supporting seat (211), and the upper end of the framework limiting block (212) is positioned right above the supporting seat (211); the upper end face of the framework limiting block (212) is used for being matched with the inner side face of the connecting beam (111) of the rudder shaft component (1), and a gap of 0.3-0.5 mm is formed between the upper end face of the framework limiting block (212) and the inner side face of the connecting beam (111); the upper end face of the framework limiting block (212) is provided with a second waist-shaped hole, one positioning pin (221) is used for connecting the pin hole on one side of the beam (111) with the second waist-shaped hole, and the other positioning pin (221) is used for connecting the pin hole on the other side of the beam (111) with the first waist-shaped hole.
2. The assembly tool for the rudder shaft type component for the ceramic matrix composite material aircraft according to claim 1, is characterized in that: the device also comprises an auxiliary limiting component;
the auxiliary limiting assembly comprises a clamping plate (213), a fixing rod (222), a pressing piece (223), a detection cushion block (224) and a horizontal limiting cushion block (225);
the fixing rod (222) is coaxially arranged with the rudder shaft (10), and the bottom end of the fixing rod (222) is fixedly connected to the bottom plate (200) and is positioned at the center of the triangular frame structure;
the pressing piece (223) is sleeved on the fixed rod (222) and is used for pressing the upper end face of the rudder shaft (10);
the detection cushion block (224) is matched with the clamping plate (213) for use, and is used for checking the profile of the rudder shaft component (1) in the assembling process;
the horizontal limiting cushion block (225) is used for being sleeved on the periphery of the rudder shaft (10), is located between the V-shaped seat (201) and the shaft sleeve (110), and is located between the supporting seat (211) and the connecting beam (111).
3. The assembly fixture for the rudder shaft type members for the ceramic-based composite material aircraft according to claim 2, characterized in that: the thickness of the horizontal limiting cushion block (225) is consistent with the total thickness of the two lower lugs (131) and the lower side beam (121);
the clamping plate (213) is provided with a plurality of lightening holes.
4. The assembly tool for the rudder shaft type component for the ceramic matrix composite material aircraft according to claim 3, is characterized in that: the fixing rod (222) is a double-end screw rod, and the pressing piece (223) comprises an end cover and a nut;
the end cover and the nut are sequentially sleeved on the double-end screw, and the end cover is tightly pressed on the upper end face of the rudder shaft (10) by screwing the nut.
5. The assembly fixture for the rudder shaft type members for the ceramic-based composite material aircraft according to claim 4, characterized in that: the V-shaped seat (201) is connected with the shaft pressing plate (202), the supporting seat (211), the framework limiting block (212) and the V-shaped seat (201) are connected with the bottom plate (200), and the connecting end of the clamping plate (213) is connected with the framework limiting block (212) through screws;
90-degree taper holes are formed in the first waist-shaped hole, the second waist-shaped hole and all the bolt connection hole positions, and the depth of each taper hole is 2-3 mm;
the shapes of two corners at the upper end of the shaft pressing plate (202) are set to be chamfers.
6. The method for assembling the rudder shaft type component for the ceramic-based composite material aircraft is characterized by comprising the following steps of:
1) preprocessing each part of the rudder shaft member (1) to ensure that the appearance of each part is clean and the size of each part reaches the standard;
2) the rudder shaft (10) is positioned and installed to ensure that the rudder shaft is stable and vertical to the bottom plate (200);
3) positioning and installing the shaft sleeve (110) and the connecting beam (111), and cementing and fixing the rudder shaft (10), the shaft sleeve (110) and the connecting beam (111):
4) positioning and mounting the shaft backing plate (112), processing the outer profile of the shaft backing plate, and grinding and finishing the shaft backing plate;
5) the front connecting arc plate (113) and the rear connecting arc plate (114) are positioned and installed;
5.1) taking the outer molded surface of the shaft backing plate (112), the upper end surface of the V-shaped seat (201) and the upper end surface of the shaft pressing plate (202) as references, installing and positioning a front connecting arc plate (113) and a rear connecting arc plate (114) to ensure that the front connecting arc plate (113) and the rear connecting arc plate (114) are respectively attached to the outer molded surface of the shaft backing plate (112), the upper end surface of the V-shaped seat (201) and the contact surface of the upper end surface of the shaft pressing plate (202);
5.2) gluing the front connecting arc plate (113) and the rear connecting arc plate (114);
5.3) respectively processing the outer profiles of the front connecting arc plate (113) and the rear connecting arc plate (114), ensuring that the profile degree is less than or equal to 0.05mm, and grinding and finishing to ensure that the profiles are smooth;
5.4) numerically controlling the upper end surface of the shaft sleeve (110) and the upper side surface of the connecting beam (111);
6) positioning and mounting the upper side beam (120);
6.1) positioning and installing an upper side beam (120) by taking the outer profile of the rudder shaft (10), the upper end surface of the shaft sleeve (110) and the upper side surface of the connecting beam (111) as references;
6.2) gluing and fixing the upper side beam (120);
7) positioning and mounting of two upper tabs (130);
7.1) taking the outer molded surface of the rudder shaft (10) and the upper end surface of the upper side beam (120) as references, sequentially positioning and installing two upper lugs (130) and carrying out gluing and fixing;
7.2) processing the upper end surface of the upper lug (130) on the outer side, ensuring flatness, reserving a wall thickness allowance of 0.5mm, and ensuring that the planeness is less than or equal to 0.05 mm;
8) positioning and mounting a lower side beam (121) and a lower lug (131);
taking down the assembly part after the step 7.2) is finished, turning around and installing the assembly part on a tool, and installing a lower side beam (121) and two lower lugs (131) according to the methods in the step 6) and the step 7);
9) mounting a skin (14) by taking the outer profile of the front connecting arc plate (113), the outer profile of the rear connecting arc plate (114) and the end face of the outer lug as references, and fixedly connecting the skin (14) with the front connecting arc plate (113), the rear connecting arc plate (114), the side beam assembly (12) and the lug assembly (13) integrally to obtain an assembled rudder shaft component (1);
10) taking the assembled rudder shaft member (1) down from the tool, and carrying out SiC matrix deposition on the appearance of the rudder shaft member (1);
11) the outer shape of the rudder shaft member (1) is superfinished to obtain the rudder shaft member (1).
7. The method for assembling the rudder shaft type component for the ceramic matrix composite aircraft according to claim 6, wherein in the step 10), SiC matrix deposition is performed through a chemical vapor infiltration process: the deposition time is 30-45 h, the deposition temperature is 850-1000 ℃, and the reaction gas is trichloromethylsilane, argon and hydrogen.
8. The method for assembling the rudder shaft type component for the ceramic matrix composite aircraft according to claim 7, wherein the step 1) is specifically as follows: the surfaces of all parts forming the rudder shaft component (1) are polished, polished and cleaned, and then are cleaned and dried, so that the appearances of all parts are ensured to have no redundant substances, and the appearances and the sizes of all parts reach the standard;
the step 2) is specifically as follows: the rudder shaft (10) is positioned and installed on the shaft positioning component (20), so that the fit clearance between the outer profile of the rudder shaft (10) and three inner side surfaces of the triangular frame structure is less than or equal to 0.05mm, and the perpendicularity between the axis of the rudder shaft (10) and the bottom plate (200) is less than or equal to 0.05/500 mm;
the step 3) is specifically as follows:
3.1) the shaft sleeve (110) is arranged on the rudder shaft (10), the fit clearance between the inner arc surface of the shaft sleeve (110) and the outer surface of the rudder shaft (10) is less than or equal to 0.05mm, and the lower end surface of the shaft sleeve (110) is tightly attached to the upper end surface of the V-shaped seat (201) and the upper end surface of the shaft pressing plate (202);
3.2) tightly attaching the outer side surface of one side of the connecting beam (111) to the upper end surface of the V-shaped seat (201) and the upper end surface of the supporting seat (211), adjusting the positions of the shaft sleeve (110) and the connecting beam (111), and ensuring that the profile of the connecting beam (111) is attached to the profile of the shaft sleeve (110); pin holes on two sides of the connecting beam (111) are respectively aligned with a second waist-shaped hole on the framework limiting block (212) and a first waist-shaped hole on the supporting seat (211), and the rudder shaft (10), the shaft sleeve (110) and the connecting beam (111) are fixed in a cementing manner;
the step 4) is specifically as follows:
4.1) installing a shaft backing plate (112) by taking the fixed shaft sleeve (110) and the connecting beam (111) as references, and ensuring that the fit clearance between the inner molded surface of the shaft backing plate (112) and the outer molded surface of the shaft sleeve (110) is less than or equal to 0.05 mm;
4.2) machining the outer profile of the shaft backing plate (112) by adopting numerical control, and ensuring that the profile tolerance of the outer profile of the shaft backing plate (112) is less than or equal to 0.05 mm; detecting the high point of the profile, and grinding and finishing to ensure that the profile of the shaft backing plate (112) is smooth;
in the step 5.1), the fit clearance between the inner profile of the front connecting arc plate (113) and the inner profile of the rear connecting arc plate (114) and the outer profile of the shaft backing plate (112) is less than or equal to 0.05 mm;
in the step 5.3), the grinding and fine trimming to ensure that the molded surface is smooth specifically comprises the following steps: detecting the high points of the molded surfaces of the front connecting arc plate (113) and the rear connecting arc plate (114), and grinding and finishing to ensure the smooth molded surfaces;
the step 6.1) is specifically as follows: the outer profile of the steering shaft (10), the upper end surface of the shaft sleeve (110) and the upper side surface of the connecting beam (111) are taken as references, the upper side beam (120) is positioned and installed, the assembling gap between the upper side beam (120) and the outer profile of the steering shaft (10) is ensured to be less than or equal to 0.1mm, and the fitting gap between the upper side beam (120) and the upper end surface of the shaft sleeve (110) and the upper side surface of the connecting beam (111) is less than or equal to 0.05 mm;
the step 7.1) is specifically as follows: the outer molded surface of the rudder shaft (10) and the upper end surface of the upper side beam (120) are taken as references, two upper lugs (130) are sequentially positioned and installed, the molded surface fit clearance between the two upper lugs (130) and between the upper lugs (130) and the upper side beam (120) is ensured to be less than or equal to 0.05mm, and the upper lugs are fixed by gluing;
the step 9) is specifically as follows: mounting a skin (14) by taking the outer profile of the front connecting arc plate (113), the outer profile of the rear connecting arc plate (114) and the end face of an outer lug as references, ensuring that the fit clearance of the skin (14) with the outer profiles of the front connecting arc plate (113) and the rear connecting arc plate (114) is less than or equal to 0.1mm, and integrally and fixedly connecting the skin (14) with the front connecting arc plate (113), the rear connecting arc plate (114), the side beam assembly (12) and the lug assembly (13) to obtain the assembled rudder shaft component (1);
the step 11) is specifically as follows: and resetting and installing the deposited rudder shaft member (1) on a tool, and carrying out numerical control superfinishing on the appearance of the rudder shaft member (1) to ensure the requirement of dimensional precision to obtain the rudder shaft member (1).
9. The method for assembling the rudder shaft type component for the ceramic matrix composite aircraft according to the claim 8, wherein in the step 3.1), horizontal limit cushion blocks (225) are placed on the upper end surface of a shaft pressing plate (202), the upper end surface of a V-shaped seat (201) and the upper end surface of a supporting seat (211), and the lower end surface of a shaft sleeve (110) is tightly attached to the upper end surface of the horizontal limit cushion blocks (225);
in the step 3.2), the outer side surface of one side of the connecting beam (111) is tightly attached to the upper end surface of the horizontal limiting cushion block (225);
in the step 5.1), the installation reference is the outer molded surface of the processed shaft base plate (112) and the upper end surface of the horizontal limiting cushion block (225); the lower end surfaces of the outer convex parts of the front connecting arc plate (113) and the rear connecting arc plate (114) are tightly attached to the upper end surface of the horizontal limiting cushion block (225);
in the step 8), after the assembly part integral and the horizontal limiting cushion block (225) which are finished in the step 7.2) are taken down, the assembly part integral is turned around and installed on a tool, and the lower side beam (121) and the two lower lug pieces (131) are installed according to the methods in the step 6) and the step 7);
in the step 4.2), the detection profile high point is detected according to the matching use of the detection cushion block (224) and the clamping plate (213).
10. The method for assembling the rudder shaft type member for the ceramic matrix composite aircraft according to claim 9, wherein the step 2) is specifically as follows: the fixing rod (222) is installed on the bottom plate (200) and located in the center of the triangular frame structure, the rudder shaft (10) is sleeved on the periphery of the fixing rod (222) and installed on the bottom plate (200), the fit clearance between the outer profile of the rudder shaft (10) and three inner side faces of the triangular frame structure is guaranteed to be smaller than or equal to 0.05mm, the verticality between the axis of the rudder shaft (10) and the bottom plate (200) is smaller than or equal to 0.05/500mm, and finally the pressing piece (223) is sleeved on the upper end of the rudder shaft (10) from the upper end of the fixing rod (22) and pressed tightly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210501700.3A CN114789415B (en) | 2022-05-09 | 2022-05-09 | Rudder shaft component assembly tool and assembly method for ceramic matrix composite aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210501700.3A CN114789415B (en) | 2022-05-09 | 2022-05-09 | Rudder shaft component assembly tool and assembly method for ceramic matrix composite aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114789415A true CN114789415A (en) | 2022-07-26 |
| CN114789415B CN114789415B (en) | 2023-07-07 |
Family
ID=82460999
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210501700.3A Active CN114789415B (en) | 2022-05-09 | 2022-05-09 | Rudder shaft component assembly tool and assembly method for ceramic matrix composite aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114789415B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB190516838A (en) * | 1905-08-19 | 1906-06-07 | Franz Wondra | Improvements in or relating to Flying Machines. |
| CN104325425A (en) * | 2014-11-05 | 2015-02-04 | 上海大学 | Fixture suitable for assembling batteries in various specifications |
| CN209439714U (en) * | 2019-01-31 | 2019-09-27 | 北京瑞通大成自动化设备有限公司 | The clamping device of motor vehicle seat back assembly tooling |
| CN112476319A (en) * | 2020-11-26 | 2021-03-12 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite material aeroengine small-sized blade assembly tool and assembly method |
| CN112645716A (en) * | 2020-12-22 | 2021-04-13 | 西安鑫垚陶瓷复合材料有限公司 | Deposition sizing tool and method for ceramic matrix composite part |
| CN114105679A (en) * | 2021-11-25 | 2022-03-01 | 西安鑫垚陶瓷复合材料有限公司 | Chemical vapor infiltration flow guide equipment and method for preparing ceramic composite pipe fitting by using same |
-
2022
- 2022-05-09 CN CN202210501700.3A patent/CN114789415B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB190516838A (en) * | 1905-08-19 | 1906-06-07 | Franz Wondra | Improvements in or relating to Flying Machines. |
| CN104325425A (en) * | 2014-11-05 | 2015-02-04 | 上海大学 | Fixture suitable for assembling batteries in various specifications |
| CN209439714U (en) * | 2019-01-31 | 2019-09-27 | 北京瑞通大成自动化设备有限公司 | The clamping device of motor vehicle seat back assembly tooling |
| CN112476319A (en) * | 2020-11-26 | 2021-03-12 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite material aeroengine small-sized blade assembly tool and assembly method |
| CN112645716A (en) * | 2020-12-22 | 2021-04-13 | 西安鑫垚陶瓷复合材料有限公司 | Deposition sizing tool and method for ceramic matrix composite part |
| CN114105679A (en) * | 2021-11-25 | 2022-03-01 | 西安鑫垚陶瓷复合材料有限公司 | Chemical vapor infiltration flow guide equipment and method for preparing ceramic composite pipe fitting by using same |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114789415B (en) | 2023-07-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20050116105A1 (en) | Determinant wing assembly | |
| CN105035354B (en) | Coordinate frock and assembly method in a kind of net side of composite material skin | |
| CN109531196B (en) | A benchmark conversion equipment for rotor blade tenon processing | |
| CN108555533B (en) | Gluing assembly method of carbon fiber composite material three-dimensional truss | |
| CN100496882C (en) | Numerically controlled clamping method and milling tool for joint parts | |
| CN114789415A (en) | Rudder shaft component assembly tool and assembly method for ceramic-based composite material aircraft | |
| CN114670085A (en) | Machining fixture and machining method for plug valve seat | |
| CN113953772B (en) | Machining method for special-shaped mounting edge of cast cone ring block | |
| WO2022179202A1 (en) | Low-stress processing method for large-size and high-precision antenna interface | |
| CN114872922A (en) | Digital assembly process method for civil aircraft framed cabin door structure assembly | |
| CN112610574B (en) | Metal reinforcing component for ceramic matrix composite material support and support assembling method | |
| CN113798789A (en) | Manufacturing process of assembly for test | |
| CN113369831A (en) | Machining process of aero-engine blade | |
| CN219853147U (en) | Be used for split type aircraft horizontal tail L type to connect finish machining frock | |
| CN110480076A (en) | A kind of honeycomb core method of processing parts based on boss fixing | |
| CN216432831U (en) | Aircraft skin appearance waviness detection device | |
| CN110394601B (en) | Numerical control machining method for multidimensional optical window part | |
| CN115582879B (en) | Honeycomb core prefabrication method | |
| CN215092149U (en) | Milling fixture | |
| CN212526924U (en) | Clamp for drilling and welding inspection of special-shaped structural part | |
| CN112427885B (en) | Method and supporting mechanism suitable for machining large thin-wall frame ring part | |
| CN117864410A (en) | Assembly tool and method for ceramic matrix composite skin hanging point structure | |
| CN113579852B (en) | Auxiliary measuring device for automatic processing of lugs and using method thereof | |
| CN220260239U (en) | Numerical control milling fixture for airplane beam parts | |
| CN113231793B (en) | Method for processing inner cavity web plate |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 710117 West Section 912 of Biyuan Road, Xi'an High-tech Zone, Shaanxi Province Patentee after: Xi'an Xinyao Ceramic Composite Co.,Ltd. Country or region after: China Address before: 710117 West Section 912 of Biyuan Road, Xi'an High-tech Zone, Shaanxi Province Patentee before: XI'AN GOLDEN MOUNTAIN CERAMIC COMPOSITES CO.,LTD. Country or region before: China |