CN109604505A - A kind of new titanium alloy material at high temperature riveting set and process - Google Patents
A kind of new titanium alloy material at high temperature riveting set and process Download PDFInfo
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- CN109604505A CN109604505A CN201811598473.0A CN201811598473A CN109604505A CN 109604505 A CN109604505 A CN 109604505A CN 201811598473 A CN201811598473 A CN 201811598473A CN 109604505 A CN109604505 A CN 109604505A
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- rivet
- riveting
- high temperature
- control unit
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Classifications
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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
-
- 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
-
- 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
- B21J15/28—Control devices specially adapted to riveting machines not restricted to one of the preceding subgroups
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Insertion Pins And Rivets (AREA)
Abstract
A kind of new titanium alloy material at high temperature riveting set and process, belong to Aeronautics and Astronautics engineer application technical field.The present invention does not have process to realize that high temperature of the Ti60 rivet in Aerospace Engineering technical field rivets application problem to solve the prior art.Technical solution of the present invention includes, Step 1: installation new titanium alloy material at high temperature riveting set, after device is powered, rivet hot parameter is inputted in main control unit, for controlling Ti60 rivet high temperature riveting process parameter；Step 2: keeping top iron stable, aircraft skin and airframe are subjected to riveting position and are combined and stick on top iron position, starts rivet hot system control unit, rivet hot system control unit controls riveting gun realization and rivets to aircraft skin and airframe；Step 3: removing riveting gun completes the riveting operation of Ti60 rivet high temperature.The mechanical properties such as stretching, shearing, inside metallographic of Ti60 rivet meet design requirement after high temperature riveting of the present invention, realize the application in high temperature aerospace engineering field.
Description
Technical field
The present invention relates to a kind of high temperature riveting process methods, belong to Aeronautics and Astronautics engineer application technical field.
Background technique
Riveting, i.e. rivet interlacement are using axial force that the rivet bar in hole in piece part is upset and form ailhead, make multiple zero
The method that part is connected.Riveted structure is applied widely, at low cost, common are the rivet of the materials such as steel or aluminum, normal
It can be riveted under temperature, referred to as cold riveting；In aeroplane structure design, to mitigate overall structure weight, it is using phase transition temperature mostly
400-600 DEG C of titanium alloy material rivet.Since titanium alloy material cold plasticity is poor, strain rate is sensitive, yield strength ratio is high, room temperature
Lower forming difficulty, and it is easy to produce crackle, therefore, for titanium alloy material rivet, general use first is heated, then carries out
The method of riveting, also referred to as rivet hot.
High-speed aircraft is in flight course, and covering and windage generate heat, these heats pass through fuselage skin and bone
Frame is conducted to rivet, and gradually changes the mechanical property of rivet；When the heat of accumulation reaches the phase transition temperature of rivet metal material
Afterwards, the mechanical property of rivet will degradation, eventually lead to fuselage skin and skeleton riveting obscission.
The prior art proposes a kind of titanium alloy material Ti60 rivet, and stable mechanical property has high temperature creep good, resistance to
The features such as high temperature, phase transition temperature are high, high temperature plasticity is good, high temperature easily shapes, but there is no a kind of maturations in the prior art
Riveting technology is used to Ti60 rivet equipping enterprising enforcement in aerospace and use, therefore is badly in need of a kind of clinching method realization Ti60 riveting
Follow closely the application on Aerospace Engineering field.
Summary of the invention
The purpose of the present invention is to solve the prior arts not to have a kind of process to realize Ti60 rivet in aerospace
High temperature in field of engineering technology rivets application problem, and then provides a kind of new titanium alloy material at high temperature riveting set and technique
Method.
The technical scheme is that
A kind of new titanium alloy material at high temperature riveting set, including rivet hot system control unit, top iron, Ti60 rivet, fly
Machine covering, spring formed punch, riveting gun, air pump and airframe, riveting gun and air pump establish connection, and air pump rivets for realizing riveting gun to be made
Industry, the front end of riveting gun have spring formed punch, the aircraft skin and airframe of riveting in need, top are arranged between riveting gun and top iron
Iron, rivet hot system control unit and the aircraft skin for needing to rivet, airframe form a closed heating circuit, rivet hot system
Heating temperature, heating voltage and the heating time parameter of control unit of uniting control high temperature riveting process, rivet hot system control unit
Connection is established by riveting circuit with riveting gun, rivet hot system control unit controls riveting time and the hammering frequency of riveting gun.
A kind of new titanium alloy material at high temperature riveting process method, comprising the following steps:
Step 1: a kind of new titanium alloy material at high temperature riveting set is installed in connection, it is after device is powered, rivet hot parameter is defeated
Enter in main control unit, for controlling Ti60 rivet high temperature riveting process parameter；
Step 2: top iron is kept to stablize, carry out the aircraft skin and airframe to rivet position being combined and paste
Top iron position is leaned against, rivet hot system control unit is started, rivet hot system control unit controls riveting gun and realizes to aircraft skin and fly
Machine skeleton carries out high temperature riveting；
Step 3: removing riveting gun completes the rivet hot operation of Ti60 rivet.
Further, rivet hot system control unit 1 controls the realization of riveting gun 6 to aircraft skin 4 and aircraft in the step 2
Skeleton 8 is riveted, and is sequentially completed following movement according to program:
Step a, aircraft skin 4 and airframe 8 act against on iron 2, and heating circuit a starting, riveting circuit b awaits orders,
Heating circuit a continuous heating Ti60 rivet, until stopping heating circuit a to Ti60 after Ti60 rivet is heated to 900-1000 DEG C
Rivet heating work；
Step b, starting riveting circuit b, rivet hot system control unit 1 control the Ti60 rivet temperature after being heated of riveting gun 6
It before decline, realizes and Ti60 rivet is hammered and is hit, during hammering and strike, top iron 2 is using riveting gun 6 to Ti60 rivet
Active force forms pier nose in rivet bottom.
Further, heating circuit a is 900-1000 DEG C to the heating temperature of Ti60 rivet in the step a.
Further, frequency is hammered in the step b according to hot rivet diameter and environmental range is 5-50Hz, is beaten
Hitting the time is 0.5-2s.
The invention has the benefit that
1, domestic for the first time to apply Ti60 material in high temperature hot riveting field；It is domestic to realize the rivet hot of Ti60 material at high temperature for the first time
It connects process and is configured with relevant parameter；Provide the connection type and composed structure of a kind of high temperature riveting control equipment；
2, the mechanical properties such as the stretching, shearing of rivet, inside metallographic meet requirement after rivet hot, realize high temperature work
The application in journey field.
Detailed description of the invention
Fig. 1 is a kind of new titanium alloy material at high temperature riveting set installation graph；
Fig. 2 is Ti60 riveting molding structural schematic diagram；
1- rivet hot system control unit, 2- push up iron, 3-Ti60 material rivet, 4- aircraft skin, 5- spring formed punch, 6- riveting
Rifle, 7- air pump, 8- airframe.
Specific embodiment
Specific embodiment 1: embodiment is described with reference to Fig. 1, a kind of new titanium alloy material that present embodiment provides
Expect high temperature riveting set, including rivet hot system control unit 1, top iron 2, Ti60 rivet 3, aircraft skin 4, spring formed punch 5, riveting gun
6, air pump 7 and airframe 8, the front end of riveting gun 6 have spring formed punch 5, and riveting gun 6 and air pump 7 establish connection, and air pump 7 is for real
Existing riveting gun rivets operation, and the aircraft skin 4 and airframe 8 of riveting in need, top iron 2, heat are arranged between riveting gun 6 and top iron 2
Riveting system control unit 1 and the aircraft skin 4 for needing to rivet, airframe 8 form a closed heating circuit a, rivet hot system
Unite control unit 1 control rivet hot process heating temperature, heating voltage and heating time parameter, rivet hot system control unit 1 with
Riveting gun 6 establishes connection by riveting circuit b, and rivet hot system control unit 1 controls riveting time and the hammering frequency of riveting gun 6.
Specific embodiment 2: illustrating present embodiment, a kind of Novel Titanium that present embodiment provides in conjunction with Fig. 1 and Fig. 2
Alloy material high temperature riveting process method, comprising the following steps:
Step 1: a kind of new titanium alloy material at high temperature riveting set is installed in connection, it is after device is powered, rivet hot parameter is defeated
Enter in main control unit 1, for controlling Ti60 rivet hot riveting technique parameter；
Step 2: top iron 2 is kept to stablize, aircraft skin 4 and airframe 8 are subjected to riveting position and are combined simultaneously
Top 2 position of iron is sticked on, rivet hot system control unit 1 is started, rivet hot system control unit 1 controls riveting gun 6 and realizes to aircraft illiteracy
Skin 4 and airframe 8 are riveted；
Step 3: removing riveting gun 6 completes the rivet hot operation of Ti60 rivet.
Specific embodiment 3: illustrating present embodiment, a kind of Novel Titanium that present embodiment provides in conjunction with Fig. 1 and Fig. 2
Alloy material high temperature riveting set, rivet hot system control unit 1 controls riveting gun 6 and realizes to 4 He of aircraft skin in the step 2
Airframe 8 is riveted, and is sequentially completed following movement according to program:
Step a, aircraft skin 4 and airframe 8 act against on iron 2, and heating circuit a starting, riveting circuit b awaits orders,
Heating circuit a continuous heating Ti60 rivet, until stopping heating circuit a to Ti60 after Ti60 rivet is heated to 900-1000 DEG C
Rivet heating work；
Step b, starting riveting circuit b, rivet hot system control unit 1 control the Ti60 rivet temperature after being heated of riveting gun 6
It before decline, realizes and Ti60 rivet is hammered and is hit, during hammering and strike, top iron 2 is using riveting gun 6 to Ti60 rivet
Active force forms pier nose in rivet bottom.
Further, heating circuit a is 900-1000 DEG C to the heating temperature of Ti60 rivet in step a.Ti60 material
Phase transformation temperature points be 1050 DEG C, when being heated to 900-1000 DEG C to Ti60 rivet, riveting hammering carried out to rivet, completes heat
Riveting, Ti60 rivet will not be undergone phase transition under 900-1000 DEG C of environment, but at this temperature, the high temperature creep of material, persistently
The performances such as property, toughness reach best；It is decreased obviously more than material property after phase transition temperature.
Aircraft is during high-speed flight, it is desirable that the new titanium alloy material-Ti60 rivet used, by aircraft skin and bone
Frame carries out 1000 DEG C or so high temperature rivetings, the external dimensional requirements of pier nose such as table 1 after riveting；And require riveting rear surface without extra
Object cannot have ablation and crackle, and inside metallographic is without blind crack etc..
1 rivet overhang of table and pier nose minimum dimension (unit: mm)
| Rivet diameter D | Overhang L | Pier nose minimum diameter Dmin | Pier nose minimum constructive height hmin |
| 3.5 | 2.45~3.5 | ≥4.9 | ≥1.05 |
| 4 | 2.8~4.0 | ≥5.6 | ≥1.2 |
| 5 | 3.5~5.0 | ≥7.0 | ≥1.5 |
Further, it is 5-50Hz, Impulse time 0.5-2s that frequency is hammered in step b.
A kind of new titanium alloy material at high temperature riveting set and process, have carried out creativeness on riveting process and have changed
Into this method has heating circuit and rivets the complete rivet hot circuit of circuit composition, the unified control of rivet hot system master unit
It makes, ensure that two circuits can work compound.During rivet hot, heating circuit elder generation continuous heating Ti60 rivet, sensor is received
After the signal for reaching set temperature to rivet temperature, stop heating immediately, rivet circuit at this time and start at once, control riveting gun exists
Before Ti60 rivet temperature drops to assigned temperature, the hammering process to the rivet head of a nail is completed, meanwhile, using riveting gun to the work of rivet
Firmly, pier nose is formed in rivet bottom with top iron；So far, entire rivet hot process is completed.
Specific embodiment 2: illustrating present embodiment, a kind of Novel Titanium that present embodiment provides in conjunction with Fig. 1 and Fig. 2
Alloy material high temperature clinching method is 4mm with diameter, for length is the Ti60 material sunk head rivet of 8mm, and enumerates same sample ruler
A variety of typical rivets of very little size are compared as material, are riveted respectively to aircraft skin and skeleton, wherein setting Ti60 material
The best riveting process parameter of matter rivet is as follows:
Ti60 material rivet: 1000 DEG C of high temperature rivetings, the heating equipment for the use of power being 2500-4000VA, setting heating
Voltage is 7.2-10V, heating time 1.5-3.5s, hammers frequency 5-50Hz, Impulse time 0.5-2s, hits air pressure 0.42-
0.7MPa。
The mechanical test of material obtains following table after passing through above-mentioned riveting and being riveted:
Material mechanics experiment tables of data after Ti60 rivet, TB2-1 rivet and GH3030 rivet TA15 rivet
| Rivet material | Tensile strength after riveting | Room temperature shear strength | High temperature shear strength | Density of material |
| Ti60 rivet | 1000MPa | 697MPa | 500℃499MPa | 4.7Kg/cm3 |
| TB2-1 rivet | 850-980MPa | 635MPa | 300℃500MPa | 4.7Kg/cm3 |
| GH3030 | 750MPa | 461MPa | 700℃250MPa | 8.4Kg/cm3 |
| TA15 rivet | 1000MPa | 603MPa | 500℃413MPa | 4.7Kg/cm3 |
In order to sufficiently disclose Ti60 rivet space industry application be can be approved, utilize high temperature creep property pair
Than Ti60 rivet and TA15 rivet, at constant pressure, in the way of electromagnetic heating, the sample of predetermined size is heated, specified
Constant temperature under test temperature, record sample changes over time and the deflection in the short transverse that generates and original relative to sample
The percentage change of height, and then analyze the material property of Ti60 rivet:
Ti60 rivet and TA15 rivet high temperature creep property comparative experiments table
Integral high temperature creep properties, persistence, breakdown strength, density of material, inoxidizability, corrosion resistance fatigue, fracture are tough
Influence factors, the Ti60 material rivet performances such as property, impact are substantially better than the other materials such as TA15.Ti60 rivet room temperature is anti-shearing strong
It spends 697MPa and is greater than required value 650MPa；Ti60 rivet high temperature shear strength 499MPa is greater than required value 400MPa, metallographic point
Analyse conclusion: rivet interior tissue is without overheat, burning and contamination phenomenon.
In carrying out Ti60 rivet heating process, heating voltage is excessive, overlong time, then be also easy to produce rivet surface blackening and
Ablation phenomen is not met using quality requirement；Heating parameters are too small, cause heating efficiency lower than radiating efficiency, can not be by rivet
It is heated to 1000 DEG C；Impulse time is too long, then crackle is also easy to produce inside rivet, and Impulse time is too short, then can not form satisfaction and want
The pier nose outer dimension asked.
This embodiment is just an exemplary description of this patent, and Ti60 material is successfully applied to lead in high temperature hot riveting
The high temperature clinching method in domain, other metal materials can also be verified by this instance method.
Claims (5)
1. a kind of new titanium alloy material at high temperature riveting process method, which comprises the following steps:
Step 1: a kind of new titanium alloy material at high temperature riveting set is installed in connection, after device is powered, rivet hot parameter is inputted and is led
It controls in unit 1, for controlling Ti60 rivet hot riveting technique parameter；
Step 2: top iron (2) is kept to stablize, aircraft skin (4) and airframe (8) are subjected to riveting position and are combined
And top iron (2) position is sticked on, start rivet hot system control unit (1), it is real that rivet hot system control unit (1) controls riveting gun (6)
Now aircraft skin (4) and airframe (8) are riveted；
Step 3: removing riveting gun (6) completes the rivet hot operation of Ti60 rivet.
2. a kind of new titanium alloy material at high temperature riveting process method according to claim 1, it is characterised in that: the step
Rivet hot system control unit (1) control riveting gun (6) is realized and is riveted to aircraft skin (4) and airframe (8) in rapid two, is pressed
Following movement is sequentially completed according to program:
Step a, aircraft skin (4) and airframe (8) act against on iron (2), and heating circuit (a) starting rivets circuit (b)
It awaits orders, heating circuit (a) continuous heating Ti60 rivet, until it is right to stop heating circuit (a) after Ti60 rivet is heated to 1000 DEG C
Ti60 rivet heating work；
Step b, starting riveting circuit (b), rivet hot system control unit (1) control riveting gun (6) Ti60 rivet temperature after being heated
It before degree decline, realizes and Ti60 rivet is hammered and is hit, during hammering and strike, top iron (2) is using riveting gun (6) to Ti60
The active force of rivet forms pier nose in rivet bottom.
3. a kind of new titanium alloy material at high temperature riveting process method according to claim 1, it is characterised in that: described
Heating circuit (a) is 900-1000 DEG C to the heating temperature of Ti60 rivet in step a.
4. a kind of new titanium alloy material at high temperature riveting process method according to claim 1, it is characterised in that: described
It is 5-50Hz, Impulse time 0.5-2s that frequency is hammered in step b.
5. a kind of new titanium alloy material at high temperature riveting set according to claim 1, it is characterised in that: including rivet hot system
It unites control unit (1), push up iron (2), Ti60 rivet (3), aircraft skin (4), spring formed punch (5), riveting gun (6), air pump (7) and fly
Connection is established in machine skeleton (8), riveting gun (6) and air pump (7), and air pump (7) rivets operation, riveting gun (6) He Dingtie for realizing riveting gun
(2) aircraft skin (4) and airframe (8) of riveting in need be set between, top iron (2), rivet hot system control unit (1) and
Aircraft skin (4), the airframe (8) for needing to rivet form a closed heating circuit (a), rivet hot system control unit
(1) heating temperature, heating voltage and the heating time parameter of rivet hot process, rivet hot system control unit (1) and riveting gun (6) are controlled
Connection is established by riveting circuit (b), rivet hot system control unit (1) controls riveting time and the hammering frequency of riveting gun (6).
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| CN201811598473.0A CN109604505A (en) | 2018-12-25 | 2018-12-25 | A kind of new titanium alloy material at high temperature riveting set and process |
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| CN201811598473.0A CN109604505A (en) | 2018-12-25 | 2018-12-25 | A kind of new titanium alloy material at high temperature riveting set and process |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111069514A (en) * | 2019-12-31 | 2020-04-28 | 湖北三江航天红阳机电有限公司 | Riveting process method for air rudder |
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