CN111069514A - Riveting process method for air rudder - Google Patents
Riveting process method for air rudder Download PDFInfo
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- CN111069514A CN111069514A CN201911410445.6A CN201911410445A CN111069514A CN 111069514 A CN111069514 A CN 111069514A CN 201911410445 A CN201911410445 A CN 201911410445A CN 111069514 A CN111069514 A CN 111069514A
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- rivet
- riveting
- titanium alloy
- rudder plate
- rudder
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J15/00—Riveting
- B21J15/02—Riveting procedures
- B21J15/08—Riveting by applying heat, e.g. to the end parts of the rivets to enable heads to be formed
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J15/00—Riveting
- B21J15/10—Riveting machines
- B21J15/14—Riveting machines specially adapted for riveting specific articles, e.g. brake lining machines
- B21J15/142—Aerospace structures
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J15/00—Riveting
- B21J15/10—Riveting machines
- B21J15/16—Drives for riveting machines; Transmission means therefor
- B21J15/18—Drives for riveting machines; Transmission means therefor operated by air pressure or other gas pressure, e.g. explosion pressure
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/32—Air braking surfaces
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- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Insertion Pins And Rivets (AREA)
- Connection Of Plates (AREA)
Abstract
The embodiment of the invention provides an air vane riveting process method, which comprises the following steps: when the titanium alloy rudder fork and the aluminum-based composite material rudder plate are riveted, a taper pin rivet is arranged in a corresponding first rivet hole on the titanium alloy rudder fork and the aluminum-based composite material rudder plate, the small end of the taper pin rivet protrudes out of the corresponding first rivet hole, the protruding part of the small end is heated, and after the small end is heated to a preset state, the small end is subjected to pneumatic riveting; when the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate are riveted, inserting a first rivet into a corresponding second rivet hole on the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate, carrying out static pressure riveting on the first rivet, and then carrying out pneumatic riveting on the first rivet; when the titanium alloy transition rudder plate and the C/SiC front edge are riveted, a second rivet is inserted into a corresponding third rivet hole on the titanium alloy transition rudder plate and the C/SiC front edge, the second rivet is subjected to static pressure riveting, and the hammer riveting is used for riveting the second rivet.
Description
Technical Field
The invention relates to the technical field of air rudders, in particular to an air rudder riveting process method.
Background
The composite material has a series of advantages of high specific strength, high specific modulus, good fatigue resistance, corrosion resistance and the like, and is widely applied to modern aerospace structures. Although the composite material has the advantages which are not possessed by common metals, the composite material also has certain weaknesses: brittleness, low interlayer strength and poor impact resistance. Aiming at composite materials, two common mechanical connection methods are bolt connection and rivet connection, and compared with screw connection, the riveting joint is light in weight and low in cost and is widely applied to modern aerospace structures.
The aluminum-based composite material air rudder consists of a titanium alloy rudder fork, an aluminum-based composite material rudder plate, a titanium alloy transition rudder plate and a carbon fiber reinforced silicon carbide C/SiC front edge, and all the parts are connected and formed through a riveting process. By adopting the original riveting mode, a series of problems of layering, damage or crack generation exist in the riveting process, and the design index cannot be met.
Disclosure of Invention
The embodiment of the invention provides an air vane riveting process method which is used for solving the problems of layering, damage, cracks and the like generated when an aluminum-based composite material air vane is riveted and formed.
The air rudder riveting process method provided by the embodiment of the invention comprises a titanium alloy rudder fork, an aluminum-based composite material rudder plate, a titanium alloy transition rudder plate and a C/SiC front edge, and the method comprises the following steps:
when the titanium alloy rudder fork and the aluminum-based composite material rudder plate are riveted, a taper pin rivet is arranged in a corresponding first rivet hole on the titanium alloy rudder fork and the aluminum-based composite material rudder plate, the small end of the taper pin rivet protrudes out of the corresponding first rivet hole, the protruding part of the small end is heated, and after the small end is heated to a preset state, the small end is subjected to pneumatic riveting;
when the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate are riveted, inserting a first rivet into a corresponding second rivet hole on the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate, carrying out static pressure riveting on the first rivet, and then carrying out pneumatic riveting on the first rivet;
when the titanium alloy transition rudder plate and the C/SiC front edge are riveted, a second rivet is inserted into a corresponding third rivet hole on the titanium alloy transition rudder plate and the C/SiC front edge, the second rivet is subjected to static pressure riveting, and the second rivet is riveted by using a hammer.
Optionally, the small end of the taper pin rivet protrudes out of the corresponding first rivet hole, and the protruding length of the small end is within the length range of 4.5 mm-5.5 mm.
Optionally, heating the protruding portion of the small end, after heating to a preset state, performing pneumatic riveting on the small end includes:
and carrying out gas welding auxiliary heating on the protruding part of the small end, adjusting the flame diameter to be within the range of 4-6 mm during gas welding auxiliary heating, keeping the single heating time for 5 seconds, keeping the temperature of the protruding part of the small end not higher than 400 ℃, and carrying out pneumatic riveting on the small end after heating until the protruding part of the small end is red or dark red.
Optionally, when the titanium alloy rudder fork and the aluminum-based composite rudder plate are riveted, the method further includes:
and riveting the titanium alloy rudder fork and the aluminum-based composite material rudder plate according to the riveting sequence of symmetrical riveting at the middle part and the two sides.
Optionally, the static pressure riveting the first rivet and then the pneumatic riveting the first rivet includes:
adjusting a static pressure machine, controlling the compression stroke of the rivet to be 0.7-0.9 mm, controlling the rivet length range of the first rivet after the static pressure riveting to be 10.8-11.2 mm, riveting by using an air gun, and controlling the pier head diameter range of the first rivet after the riveting to be 4.3-4.7 mm.
Optionally, when the aluminum matrix composite rudder plate and the titanium alloy transition rudder plate are riveted, the method further includes:
brushing a layer of epoxy resin adhesive on the contact position of the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate, and organizing the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate together;
and riveting the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate in a double-sided staggered mode.
Optionally, the static pressure riveting the second rivet includes:
and adjusting the static pressure machine, controlling the compression stroke of the rivet to be 0.7-0.9 mm, and controlling the rivet length range of the second rivet after the static pressure riveting to be 20.8-21.2 mm.
Optionally, the method further includes:
before riveting the titanium alloy rudder fork and the aluminum-based composite material rudder plate, processing first rivet holes which are distributed in a staggered mode and have the central diameter of 6mm and the Morse taper of 0 degree on the titanium alloy rudder fork and the aluminum-based composite material rudder plate;
before riveting the aluminum matrix composite rudder plate and the titanium alloy transition rudder plate, forming a plurality of second rivet holes with the diameter of 2.5mm on the titanium alloy transition rudder plate, and processing the aluminum matrix composite rudder plate through the plurality of second rivet holes with the diameter of 2.5mm to form a plurality of through holes with the diameter of 3.1mm matched with the second rivet holes;
before the titanium alloy transition rudder plate and the C/SiC front edge are riveted, a plurality of third rivet holes with the diameter of 2.5mm are formed in the titanium alloy transition rudder plate, through the third rivet holes with the diameter of 2.5mm in the titanium alloy transition rudder plate, a plurality of through holes with the diameter of 3.1mm matched with the third rivet holes are formed in the C/SiC front edge in a matched mode, and the titanium alloy transition rudder rivet holes are countersunk in a double-faced countersunk mode.
Optionally, riveting the second rivet with a hammer rivet includes:
riveting the second rivet by using a hammer so that the counter sink hole is filled with the pier head of the second rivet after the riveting is finished;
and grinding the rivet pier head to enable the head of the second rivet to be flush with the titanium alloy transition rudder plate.
Optionally, the taper pin rivet, the first rivet and the second rivet are all made of 1Cr18Ni9 Ti.
One or more technical solutions in the embodiments of the present application have at least one or more of the following technical effects:
according to the technical scheme of the embodiment of the invention, when the air rudder is riveted and formed, the titanium alloy rudder fork and the aluminum-based composite material rudder plate are riveted by adopting a hot riveting and pneumatic riveting mode, the taper pin rivet is arranged in the corresponding first rivet hole on the titanium alloy rudder fork and the aluminum-based composite material rudder plate, the small end of the taper pin rivet protrudes out of the corresponding first rivet hole, the protruding part of the small end is heated, and the small end is riveted pneumatically after the small end is heated to a preset state. And then riveting the aluminum-based composite rudder plate and the titanium alloy transition rudder plate in a static pressure and pneumatic riveting mode, inserting a first rivet into a corresponding second rivet hole on the aluminum-based composite rudder plate and the titanium alloy transition rudder plate, performing static pressure riveting on the first rivet, and then performing pneumatic riveting on the first rivet. And finally, when the titanium alloy transition rudder plate and the C/SiC front edge are riveted by adopting a static pressure and hammer riveting mode, inserting a second rivet into a corresponding third rivet hole on the titanium alloy transition rudder plate and the C/SiC front edge, carrying out static pressure riveting on the second rivet, and riveting the second rivet by using the hammer riveting. According to the riveting method, the adaptive riveting mode is selected according to the characteristics and the structural characteristics of the composite material, and through verification, the problems of layering, damage, cracks and the like in the riveting forming process of the aluminum-based composite material air rudder are effectively solved, and the riveting quality and precision of the aluminum-based composite material air rudder are ensured.
Drawings
Fig. 1 is a flowchart of an air vane riveting process method provided in an embodiment of the present application;
fig. 2 is a schematic view of an air vane riveting provided in an embodiment of the present application.
Detailed Description
The embodiment of the invention provides an air vane riveting process method which is used for solving the problems of layering, damage, cracks and the like generated when an aluminum-based composite material air vane is riveted and formed. The air rudder comprises a titanium alloy rudder fork, an aluminum-based composite material rudder plate, a titanium alloy transition rudder plate and a C/SiC front edge, and the method comprises the following steps: when the titanium alloy rudder fork and the aluminum-based composite material rudder plate are riveted, a taper pin rivet is arranged in a corresponding first rivet hole on the titanium alloy rudder fork and the aluminum-based composite material rudder plate, the small end of the taper pin rivet protrudes out of the corresponding first rivet hole, the protruding part of the small end is heated, and after the small end is heated to a preset state, the small end is subjected to pneumatic riveting; when the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate are riveted, inserting a first rivet into a corresponding second rivet hole on the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate, carrying out static pressure riveting on the first rivet, and then carrying out pneumatic riveting on the first rivet; when the titanium alloy transition rudder plate and the C/SiC front edge are riveted, a second rivet is inserted into a corresponding third rivet hole on the titanium alloy transition rudder plate and the C/SiC front edge, the second rivet is subjected to static pressure riveting, and the second rivet is riveted by using a hammer.
The technical solutions of the present invention are described in detail below with reference to the drawings and specific embodiments, and it should be understood that the specific features in the embodiments and examples of the present invention are described in detail in the technical solutions of the present application, and are not limited to the technical solutions of the present application, and the technical features in the embodiments and examples of the present application may be combined with each other without conflict.
The term "and/or" herein is merely an association describing an associated object, meaning that three relationships may exist, e.g., a and/or B, may mean: a exists alone, A and B exist simultaneously, and B exists alone. In addition, the character "/" herein generally indicates that the former and latter related objects are in an "or" relationship.
Referring to fig. 1, an embodiment of the present invention provides an air rudder riveting process method, where the air rudder includes a titanium alloy rudder fork, an aluminum-based composite material rudder plate, a titanium alloy transition rudder plate, and a C/SiC front edge, and the process method includes the following steps:
s101: when the titanium alloy rudder fork and the aluminum-based composite material rudder plate are riveted, a taper pin rivet is arranged in a corresponding first rivet hole on the titanium alloy rudder fork and the aluminum-based composite material rudder plate, the small end of the taper pin rivet protrudes out of the corresponding first rivet hole, the protruding part of the small end is heated, and after the small end is heated to a preset state, the small end is subjected to pneumatic riveting;
s102: when the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate are riveted, inserting a first rivet into a corresponding second rivet hole on the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate, carrying out static pressure riveting on the first rivet, and then carrying out pneumatic riveting on the first rivet;
s103: when the titanium alloy transition rudder plate and the C/SiC front edge are riveted, a second rivet is inserted into a corresponding third rivet hole on the titanium alloy transition rudder plate and the C/SiC front edge, the second rivet is subjected to static pressure riveting, and the second rivet is riveted by using a hammer.
Specifically, in this embodiment, a proper riveting method needs to be selected to rivet the components of the air vane according to the material of the components, so as to solve the problems of delamination, damage, cracks and the like caused in the riveting forming process.
First, the method in this embodiment requires a preparation work before the riveting process of the air vane is performed. Specifically, the redundancy control includes:
cleaning the redundant materials on the titanium alloy rudder fork by dipping white silk cloth with alcohol, and airing;
wiping the aluminum matrix composite rudder plate by using dry white silk cloth, and cleaning dust on the surface;
wiping the surface of the measuring platform, which needs to be used, by using white silk cloth dipped with alcohol, and airing;
in the whole production process, the product can not be directly contacted, and white gloves are needed to be worn.
Referring to fig. 2, fig. 2 is a schematic view of an air rudder riveting provided in the embodiment of the present application.
After the preparation work is completed, the riveting process method in the embodiment is executed, step S101 in the embodiment is executed, and the titanium alloy rudder fork and the aluminum-based composite material rudder plate are riveted.
Specifically, the riveting of the titanium alloy rudder fork and the aluminum-based composite material rudder plate is divided into the following processes:
first part, trial assembly. Firstly, a trial assembly process is carried out, the titanium alloy rudder fork and the aluminum-based composite material rudder plate are assembled firstly, the installation process is required to be free of interference, and then the titanium alloy rudder fork and the aluminum-based composite material rudder plate are fixed by the bow-shaped clamp after the trial assembly is completed.
And a second part, measuring detection. And then, measuring, namely placing the combined titanium alloy rudder fork and the aluminum-based composite material rudder plate on a platform, wherein the following measurement sizes meet the requirements: measuring the distance between the center of the rudder shaft and the rear wall of the rudder by using the height dimension to meet the requirement; the verticality between the rudder shaft and the bottom surface of the rudder measured by the square ruler meets the requirement.
And a third part, positioning riveting. When positioning riveting is carried out, positioning holes need to be made first. Specifically, under the firm no not hard up condition of inspection bow clamp fixed titanium alloy rudder fork and aluminium base composite material rudder plate, join in marriage through-hole that 2 departments phi 4.1mm were worked out to aluminium base composite material rudder plate through the hole that diameter is phi 4mm on the titanium alloy rudder fork, these two pairs of through-holes are applicable to the riveting location, through these 2 pairs of through-holes promptly, can be in the same place titanium alloy rudder fork and aluminium base composite material rudder plate are fixed, the subsequent riveting technology of being convenient for. And then positioning and riveting, specifically, removing the bow-shaped clamp, inserting a process rivet into the positioning hole, and riveting the titanium alloy rudder fork and the aluminum-based composite material rudder plate into a whole, wherein the process rivet is a detachable rivet for assembling and positioning. After riveting is finished, the titanium alloy rudder fork and the aluminum-based composite material rudder plate are checked to be firmly and reliably riveted, the phenomenon of looseness is avoided, the aluminum-based composite material rudder plate is checked to be good in appearance quality, no damage is caused, and the titanium alloy rudder fork is checked to have no other riveting and damage traces except the riveting position.
And the fourth part is used for processing a riveting taper hole. Specifically, the method comprises the following steps: and processing the titanium alloy rudder fork and the aluminum-based composite material rudder plate to form first rivet holes which are distributed in a staggered mode and have the center diameter of 6mm and the Morse taper of 0 degree.
Specifically, in this embodiment, a copper wire is used for cutting, or a numerical control mill is used for processing a titanium alloy rudder fork and an aluminum-based composite rudder plate to form a through hole with a center diameter of phi 6mm and a morse taper of 0 degree as a first rivet hole, and the first rivet holes are distributed in a staggered manner. The aluminum-based composite material is coated by kraft paper before processing, and because the aluminum-based composite material rudder plate can not contact water stains, and cooling liquid used in the processing process of the conical rivet hole can be remained in a gap between the titanium alloy rudder fork and the aluminum-based composite material rudder plate, the phenomenon of redundant liquid permeation is caused to the product after riveting is completed, and the heat-proof layer compounding of a subsequent product is influenced. Therefore, the aqueous coolant cannot be used in the processing. And then riveting the small end socket of the taper hole. And after the parts are matched and processed, decomposing the product, cleaning residues on the surface, drying the product at 60 ℃ for 12 hours, and riveting.
And finally, riveting the titanium alloy rudder fork and the aluminum-based composite material rudder plate finally after the above working procedures are finished.
Firstly, the taper pin rivet is arranged in the first rivet hole, and the taper pin rivet is tightly knocked from the large end by using a riveter, and the riveting is not needed. The protruding end face of the rivet is too short in size, the rivet is prone to being filled in the counter sink hole, the protruding end face is too long in size, the middle of the rivet is prone to being bent and is difficult to rivet, and therefore the protruding size of the small end of the taper pin rivet is checked after the rivet is knocked down, and the protruding size is required to meet the requirements of 4.5 mm-5.5 mm.
And then, measuring the distance between the center of the rudder shaft and the rear wall of the rudder and measuring the verticality between the rudder shaft and the bottom surface of the rudder.
Further, in order to reduce deformation, the riveting of the titanium alloy rudder fork and the aluminum-based composite material rudder plate should follow the riveting mode of symmetrical riveting of the middle and the two sides: after riveting the middle rivet (without riveting in place), selecting rivets on two sides of the middle rivet for riveting (without riveting in place), then riveting towards two sides in sequence until all single-sided rivets are riveted, and finally finishing final riveting of the rivets in sequence.
Finally, when riveting the titanium alloy rudder fork and the aluminum-based composite material rudder plate, a hot riveting combination starting riveting mode is adopted, the titanium alloy rudder fork and the aluminum-based composite material rudder plate are riveted by an air gun, a rivet head needs to be heated in the riveting process, the rivet is difficult to rivet due to too low heating temperature, and the product is easily damaged due to too high heating temperature. And only riveting the small end of the rivet in the riveting process, and only performing gas welding auxiliary heating on the protruding part of the small end of the rivet, wherein the flame diameter is adjusted to phi 4 mm-phi 6mm during the gas welding auxiliary heating process, preferably 5 seconds in a single time, and the heating is stopped when the head of the rivet (until the root of the head of the rivet) is red or dark red. And during heating, an infrared thermometer is used for measuring the temperature of the product body, and the temperature is required to be not higher than 400 ℃. No heating is allowed during the riveting stroke.
And after the titanium alloy rudder fork and the aluminum-based composite material rudder plate are riveted, executing the step S102, and riveting the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate.
Specifically, the riveting of the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate is divided into the following processes:
first part, trial assembly. Firstly, a trial assembly process is carried out, the aluminum matrix composite rudder plate and the titanium alloy transition rudder plate are trial assembled, and the gap between the aluminum matrix composite rudder plate and the titanium alloy transition rudder plate is required to be smaller than 0.3mm when the aluminum matrix composite rudder plate and the titanium alloy transition rudder plate are checked.
A second portion, a locating rivet. When positioning riveting is carried out, positioning holes need to be made first. Specifically, a hole with the diameter of phi 2.6mm is machined at the position of 2 on the aluminum matrix composite rudder plate through a hole with the diameter of phi 2.5mm on the titanium alloy transition rudder plate, and 2 holes close to the edge are selected at the position of the hole machining. Riveting the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate into a whole by using the process rivet, and checking that the gap between the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate is not more than 0.3mm after riveting.
The third part, processing second rivet hole, it is specific, including the step: it is right aluminium base combined material rudder plate with before the titanium alloy transition rudder plate riveted, form a plurality of second rivet holes that the diameter is 2.5mm on the titanium alloy transition rudder plate, through a plurality of diameters on the titanium alloy transition rudder plate are 2.5mm second rivet holes, to join in marriage on the aluminium base combined material rudder plate and form the diameter be a plurality of 3.1mm with the through-hole that the second rivet hole pairs.
Specifically, in this embodiment, 11 through holes with a diameter of 3.1mm of the aluminum matrix composite rudder plate are processed through holes with a diameter of 2.5mm at the rest positions on the titanium alloy transition rudder plate, the aluminum matrix composite rudder plate is positioned by using the spring bayonet lock, the rivet with a diameter of 2.5mm at the 2 position is removed, and the through holes with a diameter of 2.5mm at the two positions are processed into through holes with a diameter of 3.1 mm.
And finally, riveting the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate finally after the above working procedures are finished.
Specifically, firstly, a layer of epoxy resin adhesive is coated on the contact position of the aluminum matrix composite rudder plate and the titanium alloy transition rudder plate, and the aluminum matrix composite rudder plate and the titanium alloy transition rudder plate are organized together. Then, the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate are riveted together by using a first rivet in a double-sided staggered mode. Vibration between products is easy to damage the aluminum-based composite rudder plate in the riveting process, so that the riveting adopts a static pressure and air gun riveting mode, the static pressure riveting mode is firstly adopted to eliminate the gap between riveting pieces, and the static pressure machine is adjusted to control the compression stroke of the rivet to be 0.8mm +/-0.1 mm. The length of the rivet is required to be 11mm +/-0.2 mm after the static pressure riveting is finished. And then riveting by using an air gun, wherein the diameter of the pier head is required to be phi 4.5mm +/-0.2 mm after the riveting is finished.
After riveting of the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate is completed, an outer heat-proof layer is compounded outside the assembled air rudder assembly (the front edge is not assembled). Then, step S103 is executed to rivet the titanium alloy transition rudder plate and the C/SiC leading edge.
Specifically, the riveting of the titanium alloy transition rudder plate and the C/SiC front edge is divided into the following processes:
first part, trial assembly. Firstly, a trial assembly process is carried out, a titanium alloy transition rudder plate and the C/SiC front edge are trial assembled, and the gap between the titanium alloy transition rudder plate and the C/SiC front edge is required to be smaller than 0.3mm when the titanium alloy transition rudder plate and the C/SiC front edge are checked.
A second portion, a locating rivet. When positioning riveting is carried out, positioning holes need to be made first. Specifically, a hole with the diameter of phi 2.5mm on the titanium alloy transition rudder plate is matched with a hole with the diameter of phi 2.6mm at the position of the C/SiC front edge, and the 2 nd hole close to the edge is selected as the hole matching and processing position. And riveting the C/SiC front edge and the titanium alloy transition rudder plate into a whole by using a process rivet, and checking that the gap between the C/SiC front edge and the titanium alloy transition rudder plate is not more than 0.3mm after riveting.
The third part, processing third rivet hole, it is specific, including the step: before the titanium alloy transition rudder plate and the C/SiC front edge are riveted, a plurality of third rivet holes with the diameter of 2.5mm are formed in the titanium alloy transition rudder plate, through the third rivet holes with the diameter of 2.5mm in the titanium alloy transition rudder plate, a plurality of through holes with the diameter of 3.1mm matched with the third rivet holes are formed in the C/SiC front edge in a matched mode, and the titanium alloy transition rudder rivet holes are countersunk in a double-faced countersunk mode.
Specifically, in this embodiment, the C/SiC front edge is machined through the holes with the diameter of phi 2.5mm on the titanium alloy transition rudder plate, the through holes with the diameter of phi 3.1mm are formed in the positions of 8, then the spring bayonet is used for positioning, the rivets in the positioning holes with the diameter of phi 2.5mm in the positions of 2 are removed, the holes with the diameter of phi 2.5mm in the two positions are machined into the through holes with the diameter of phi 3.1mm, and the rivet holes of the titanium alloy transition rudder are reamed in a double-faced reaming manner.
And finally, after the steps are finished, carrying out final riveting on the titanium alloy transition rudder plate and the front edge of the C/SiC.
Specifically, firstly, a layer of epoxy resin glue is coated at the contact position of the C/SiC front edge and the titanium alloy transition rudder plate, the C/SiC front edge and the titanium alloy transition rudder plate are organized together, and then the C/SiC front edge and the titanium alloy transition rudder plate are riveted together by using a second rivet made of 1Cr18Ni9Ti in a cross riveting mode. During riveting, a static pressure riveting mode is firstly adopted, and a static pressure machine is adjusted to control the compression stroke of the rivet to be 0.8mm +/-0.1 mm. The length of the rivet is required to be 21mm +/-0.2 mm after riveting is finished. And riveting by using a hammer, and after the riveting is finished, the counter sinking hole is required to be filled with the pier head. And after the riveting is finished, polishing the rivet pier head to enable the rivet head to be connected with the titanium alloy transition rudder plate in a flat mode.
In this embodiment, the rivet made of 1Cr18Ni9Ti material can be used for the rivet. 1Cr18Ni9Ti is an austenitic stainless steel. 1, 18 and 9 in the 1Cr18Ni9Ti respectively represent the contents of carbon (one thousandth), chromium (%), and nickel (%), and the alloy has good plasticity, toughness and cold workability in a solid solution state, and has good corrosion resistance in a medium such as oxidizing acid, water, atmosphere and the like.
In the riveting process method of the aluminum-based composite material air rudder in the embodiment, the setting of riveting parameters such as the rivet material, the riveting mode, the riveting process, the riveting hole manufacturing, the rivet extending amount and the like is considered as the key of the air rudder forming. Therefore, the rivet material used was 1Cr18Ni9 Ti. The method comprises the steps of riveting a titanium alloy rudder fork and an aluminum-based composite material rudder plate by adopting a hot riveting and pneumatic riveting mode, installing taper pin rivets in corresponding first rivet holes on the titanium alloy rudder fork and the aluminum-based composite material rudder plate, heating the protruding parts of the small ends by protruding the corresponding first rivet holes, and carrying out pneumatic riveting on the small ends after heating to a preset state. And then riveting the aluminum-based composite rudder plate and the titanium alloy transition rudder plate in a static pressure and pneumatic riveting mode, inserting a first rivet into a corresponding second rivet hole on the aluminum-based composite rudder plate and the titanium alloy transition rudder plate, performing static pressure riveting on the first rivet, and then performing pneumatic riveting on the first rivet. And finally, when the titanium alloy transition rudder plate and the C/SiC front edge are riveted by adopting a static pressure and hammer riveting mode, inserting a second rivet into a corresponding third rivet hole on the titanium alloy transition rudder plate and the C/SiC front edge, carrying out static pressure riveting on the second rivet, and riveting the second rivet by using the hammer riveting. According to the riveting method, the adaptive riveting mode is selected according to the characteristics and the structural characteristics of the composite material, and through verification, the problems of layering, damage, cracks and the like in the riveting forming process of the aluminum-based composite material air rudder are effectively solved, and the riveting quality and precision of the aluminum-based composite material air rudder are ensured.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the invention.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (10)
1. The riveting process method for the air rudder comprises a titanium alloy rudder fork, an aluminum-based composite material rudder plate, a titanium alloy transition rudder plate and a C/SiC front edge, and is characterized by comprising the following steps of:
when the titanium alloy rudder fork and the aluminum-based composite material rudder plate are riveted, a taper pin rivet is arranged in a corresponding first rivet hole on the titanium alloy rudder fork and the aluminum-based composite material rudder plate, the small end of the taper pin rivet protrudes out of the corresponding first rivet hole, the protruding part of the small end is heated, and after the small end is heated to a preset state, the small end is subjected to pneumatic riveting;
when the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate are riveted, inserting a first rivet into a corresponding second rivet hole on the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate, carrying out static pressure riveting on the first rivet, and then carrying out pneumatic riveting on the first rivet;
when the titanium alloy transition rudder plate and the C/SiC front edge are riveted, a second rivet is inserted into a corresponding third rivet hole on the titanium alloy transition rudder plate and the C/SiC front edge, the second rivet is subjected to static pressure riveting, and the second rivet is riveted by using a hammer.
2. The method of claim 1 wherein the small end of the taper pin rivet protrudes through the corresponding first rivet hole by a length in the range of 4.5mm to 5.5 mm.
3. The method of claim 1, wherein said heating the protruding portion of the small end and after heating to a predetermined state, pneumatically riveting the small end comprises:
and carrying out gas welding auxiliary heating on the protruding part of the small end, adjusting the flame diameter to be within the range of 4-6 mm during gas welding auxiliary heating, keeping the single heating time for 5 seconds, keeping the temperature of the protruding part of the small end not higher than 400 ℃, and carrying out pneumatic riveting on the small end after heating until the protruding part of the small end is red or dark red.
4. The method of claim 1, wherein in riveting the titanium alloy rudder fork and the aluminum matrix composite rudder plate, the method further comprises:
and riveting the titanium alloy rudder fork and the aluminum-based composite material rudder plate according to the riveting sequence of symmetrical riveting at the middle part and the two sides.
5. The method of claim 1, wherein said static riveting said first rivet followed by pneumatic riveting said first rivet comprises:
adjusting a static pressure machine, controlling the compression stroke of the rivet to be 0.7-0.9 mm, controlling the rivet length range of the first rivet after the static pressure riveting to be 10.8-11.2 mm, riveting by using an air gun, and controlling the pier head diameter range of the first rivet after the riveting to be 4.3-4.7 mm.
6. The method of claim 1, wherein in riveting the aluminum matrix composite rudder plate and the titanium alloy transition rudder plate, the method further comprises:
brushing a layer of epoxy resin adhesive on the contact position of the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate, and organizing the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate together;
and riveting the aluminum-based composite material rudder plate and the titanium alloy transition rudder plate in a double-sided staggered mode.
7. The method of claim 1, wherein said static riveting said second rivet comprises:
and adjusting the static pressure machine, controlling the compression stroke of the rivet to be 0.7-0.9 mm, and controlling the rivet length range of the second rivet after the static pressure riveting to be 20.8-21.2 mm.
8. The method of claim 1, wherein the method further comprises:
before riveting the titanium alloy rudder fork and the aluminum-based composite material rudder plate, processing first rivet holes which are distributed in a staggered mode and have the central diameter of 6mm and the Morse taper of 0 degree on the titanium alloy rudder fork and the aluminum-based composite material rudder plate;
before riveting the aluminum matrix composite rudder plate and the titanium alloy transition rudder plate, forming a plurality of second rivet holes with the diameter of 2.5mm on the titanium alloy transition rudder plate, and processing the aluminum matrix composite rudder plate through the plurality of second rivet holes with the diameter of 2.5mm to form a plurality of through holes with the diameter of 3.1mm matched with the second rivet holes;
before the titanium alloy transition rudder plate and the C/SiC front edge are riveted, a plurality of third rivet holes with the diameter of 2.5mm are formed in the titanium alloy transition rudder plate, through the third rivet holes with the diameter of 2.5mm in the titanium alloy transition rudder plate, a plurality of through holes with the diameter of 3.1mm matched with the third rivet holes are formed in the C/SiC front edge in a matched mode, and the titanium alloy transition rudder rivet holes are countersunk in a double-faced countersunk mode.
9. The method of claim 8, wherein said riveting said second rivet with hammer riveting comprises:
riveting the second rivet by using a hammer so that the counter sink hole is filled with the pier head of the second rivet after the riveting is finished;
and grinding the rivet pier head to enable the head of the second rivet to be flush with the titanium alloy transition rudder plate.
10. The method of any one of claims 1-9, wherein the taper pin rivet, the first rivet, and the second rivet are all made of a material 1Cr18Ni9 Ti.
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