CN1361039A - Fast repair technique and apparatus for damaged composite material in aircraft structure - Google Patents
Fast repair technique and apparatus for damaged composite material in aircraft structure Download PDFInfo
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- CN1361039A CN1361039A CN02112607A CN02112607A CN1361039A CN 1361039 A CN1361039 A CN 1361039A CN 02112607 A CN02112607 A CN 02112607A CN 02112607 A CN02112607 A CN 02112607A CN 1361039 A CN1361039 A CN 1361039A
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- microwave
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- power source
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Abstract
The present invention relates to the repair of damaged aircraft structure and first aid repair of war damage technology. The fast repair apparatus includes one microwave power source comprising controllable autotransformer, rectifier circuit, control circuit and magnetron and one microwave applying unit comprising converter, coaxial cable and radiation antenna. The fast repair apparatus can heat the damaged part of aircraft in very short time and has no effect on the peripheral parts, so as to repair the damaged part fast and effectively.
Description
Technical field
Aircraft structural damage composite material microwave fast repair technique of the present invention and equipment belong to aircraft structural damage reparation and war wound damage repair technology.
Background technology
Because stress corrosion is with tired, and the impact of exotic, is easy to generate crackle and damage on the active service metal aeroplane.China outfield restorative procedure commonly used is to change damaged structure or use the metal reinforcement plate to rivet, weld or be glued onto damage location at present.The shortcoming of this traditional restorative procedure of continuing to use for many years is that structural weight is increased, and joint efficiency reduces greatly.Employing is spirally connected or when riveting, will forms new area of stress concentration, is difficult to realize the effective reparation to injured structure, even more serious shortcoming is that the repair time is long, repair with structure spare part preparation difficulty, repairing work operation inconvenience can't realize " repairing fast " under the condition of external field at all.It has become influences the serious problems that aircraft is repaired normal flight fast or lengthened the life, and is the key point that air force and department of civil aviaton need to be resolved hurrily.
Along with the Application and Development of composite material, performance-oriented composite material directly is glued onto the damage location of metal aeroplane as novel connector, abroad achieve success.The application composite material is repaired and is made large quantities of aircrafts recover the performance of flight, has prolonged the life-span, has obtained the economic effects of highly significant.US military particularly systematically to tracking test after the endurance crack of aircraft wing crossbeams such as Boeing 707 and C130 and the reparation that stress corrosion cracking reaches 8 years, has been verified the reliability of " repairing metal construction with composite material ".But when being engaged in this work, be still the hot sticky method of the traditional repairing composite material damaged structure of utilization abroad.Because the metallo-heat conductivility is significantly different with composite material, when adopting hot sticky method, the heat affected zone problem is difficult for solving, thereby cause external equipment to increase, the repair apparatus complexity, maintenance environmental requirement harshness is difficult to realize the outfield reparation of active service aircraft, more is difficult to release as the effective means of " repairing fast ".
Traditional repairing method of composite material such as riveting (spiral shell) connect, bonding, ultrasonic bond, friction weldering, resistance heat, induction mode Far-infrared Heating, though differ from one another, weak point are arranged all, are difficult to reach the purpose of quick reparation.Resin matrix composite are repaired the metal orthodox method, all are difficult to reach the purpose of quick reparation, as bonding process, often need long (heating, pressurization) cure time.Vulcanize " heat affected zone " problem of method, get over serious because of cure time is oversize.Infrared or far warm inertia is big, and bite difference and connection effect are undesirable.
The application of microwave technology aspect Composite Preparation and reparation, though abroad reported successively since mid-term from the eighties, but the category that often is limited to " radiation heating ", and bias toward connection and the reparation problem of microwave technology in Composite Preparation (curing) process, and composite material and structure thereof the composite material outfield of the metal construction microwave technology of repairing does not fast particularly relate in the external report as yet.Equally, present domestic engineering circle also often is summed up as " radiation heating " when the applied microwave technology, thereby causes external equipment to increase, and investment increases, and can not adapt at the quick needs of repairing of line products and metal construction outfield.
Summary of the invention
Technical matters to be solved by this invention is, develop a kind ofly can carry out the outfield to the crackle of Flight Vehicle Structure or damage location and repair fast, and repairing quality is reliable, and is practical, composite technology easy and simple to handle and equipment.For solving this technical matters, the present invention is made up of microwave power source and microwave applicator, wherein microwave power source is connected in axitron by controlled autotransformer secondary through rectifying circuit, automatic control circuit is connected in former limit of controlled autotransformer and the former limit of magnetron power source voltage transformer, the magnetron power source voltage transformer provides the power supply of axitron, the microwave applicator that links to each other with the mouth of microwave power source links to each other with radiating antenna after being connected in coaxial feeder by adapter again.
The low power microwave energy that utilizes microwave power source of the present invention to provide, through microwave applicator Flight Vehicle Structure crackle or the damage location that scribbles the high performance microwave structural adhesion carried out selectable local warming, the purpose of reach fast, high-quality being repaired Flight Vehicle Structure crackle or damage.Mainly be based on 2 mechanism: the first, place the material in the microwave field can absorb microwave energy and what absorb, depend on the character (ε of material itself fully
rAnd t
gδ), i.e. the conductive magnetism rate of material.This is the weak point of microwave as the general heating source, but also just as the composite material reparation with the advantage of power source, it can make repairs or the heating and do not influence other position rapidly of resin that the bonding pad need be solidified; Also can obtain high energy (absorption) efficient and good repairing quality, not have the anxiety of what is called " heat affected zone " for the position that does not need to heat by using microwave glue (having injected the adhesives of microwave absorption or " chiral molecules ") to improve the conductive magnetism rate of repairing district (bonding pad); It two is, the microwave energy of dielectric absorption, change rapidly with the variation of the electric field intensity (E) of microwave power source and radiation frequency (f), " the field intensity high temperature " of microwave pyrogenicity that Here it is and the characteristic of " high-frequency high temperature ", it is little that this characteristic has guaranteed that microwave pyrogenicity has thermal inertia, and the strong advantage of bite can make heated medium moment intensification, helps realizing repairing the fast control heating in district.
In addition, microwave radiation has strengthened bonding between adhesion agent and the matrix.Chemical change between the high-polymer molecular that radiation causes will cause that the physical property of poly-mer and engineering properties etc. significantly improve.For example, microwave radiation makes first molecule of poly-mer on average generate an about crosslinked unit, and consequently the viscosity of poly-mer has increased greatly, and thus, the non-thermal effect of microwave is to repair to distinguish the key point that has than the strong interface combination.Microwave radiation causes the strenuous exercise of polar group, makes to repair to distinguish son or molecule segment exchange penetration, and is producing higher degree of crosslinking at the interface, and cause the disappearance of phase interface, thereby form firm combination.
In addition, inject the way of microwave absorption by repairing district (bonding pad), improve the conductive magnetism rate of repairing district's material, thereby make " pyrogenicity fast " of microwave, " moment intensification " effect is able to realize in composite material reparation district.Adhesion agent microwave curing mechanism studies show that, because microwave heating is a kind of body heating, and its temperature traverse gradient is that internal temperature is higher than surface temperature, therefore do not exist general method of heating to form the mechanism of internal stress; Simultaneously, the conventional heating of microwave heating is more even, thereby can not cause the concentration of local of thermal stress, can not cause the local crosslinked stress concentration that excessively makes yet, so, when adopting microwave curing, both can reach the purpose of quick curing (tens of seconds or several minutes), can make again that curing is more complete, more abundant, adhesive strength is higher.
Based on above-mentioned mechanism, the present invention can to the crackle of aircraft (aircraft) structure or damage location carry out the outfield fast, high-quality, reliably, repair efficiently, make it in tens of seconds or several minutes, to form new more strong interface, to damage or defective is repaired (connection) fast and solidified, realize the purpose in outfield " repairing fast " the crackle or the damage location of aircaft configuration and other Flight Vehicle Structure.Therefore, will further improve the quick repairing ability of all kinds of aircaft configurations in the Future in China war or other Flight Vehicle Structure war wound.
Description of drawings
Fig. 1, microwave power source electrical schematic diagram.
The structural representation of Fig. 2, microwave applicator.
Label title among Fig. 2: 1, adapter, 2, coaxial feeder, 3, radiating antenna.
Radiating antenna structural representation in Fig. 3, the tube chamber.
Fig. 4, surface emissivity antenna structure view.
Fig. 5, microwave fettling knife structural representation.
Fig. 6, traveling-wave field antenna structure view.
Fig. 7, resonant cavity applicator antenna structure view.
The specific embodiment
Fig. 1 is a special microwave power source of the present invention, provide the anode voltage of axitron M by controlled autotransformer B1 behind bridge rectifier, and voltage transformer B2 provides the filament voltage of axitron M.Control circuit is by time relay J
SA, J
SS, push switch K and foot-operated switch TK form.It has automatic protection functions: i.e. J
SAAxitron M high pressure delay protection is provided; And J
SSAxitron M adjustable delay open circuit protection is provided, controls the work-hours of axitron M, and point out with audible indication by buzzer phone FM by it.Axitron M is a core component, the microwave radiation frequency is determined by it, repair for the ease of the outfield, adopt emissive power to reach 200W, frequency of operation reaches the continuous microwave oscillator of 2450MHZ, (also can adopt emissive power in case of necessity greater than 500W, frequency of operation 2450 or 915MHZ adopt coaxial cable output, during more than or equal to 500W during less than 200W, axitron is waveguide output, adopts the output of waveguide one coaxial cable adapter).When axitron M worked, output was no more than the microwave energy of 200W.Change voltage transformer B1 primary voltage, the anode voltage of may command axitron M, thus change output microwave power size.The characteristics of this microwave power source are:
1, circuit is simple, and is easy to operate, cooperates microwave applicator of the present invention microwave energy can be focused on and repaiied
The part at multiple position, thus effectively utilize the low power microwave emission and reach quick reparation aircraft crackle
Or the purpose of damage location;
2, utilize the initial straight line segment of the plate characteristic curve of axitron M, thereby make the operating voltage of axitron M
Reduce to 1000V by 1800V, guaranteed safety;
3, designed the autotransformer B of low pressure regulation and control
1Thereby, guaranteed to adopt 8 frequency-selective switch to make axitron
Safety when the M anode voltage switches has been saved indispensable high-voltage regulator in the general microwave machine.
4, when axitron be guided wave when output (generally its emissive power surpasses 500W) the present invention special guided wave one
-coaxial adapter changes it into coaxial cable output, so that be connected with applicator.
Fig. 2 is the structural representation of microwave applicator of the present invention.Can under the low power microwave radiation, satisfy the requirement that the metal aeroplane structural composite material is repaired fast.Formed by adapter 1, coaxial feeder 2 and radiating antenna 3.Adapter 1 adopts radio-frequency (RF) coaxial conversion head or standard coaxial plug, realizes being connected of microwave applicator and microwave power source by its.The input impedance matching of the characteristic impedance of coaxial feeder 2 and radiating antenna 3.It can be one section radio frequency cable, also can be the hard coaxial line that satisfies impedance match.Radiating antenna 3 is critical components of microwave applicator, and the form according to repairing district's crackle or damage location can adopt the needle-like monopole, and electric dipole or microstrip antenna are made implanted, polytypes such as direct contact type or space radiation formula.Fig. 3-the 7th, several representative type radiating antenna structural representations.
Fig. 3 is a tube chamber radiating antenna structural representation.Two kinds of fundamental types of needle-like monopole antenna and electrical dipole antenna are arranged, can insert and carry out microwave radiation in the tube chamber, Fig. 3 (a) is a needle-like monopole antenna structural representation, it is by with feeder line internal and external conductor 4,5, metallic sheath 7, needle-like monopole 6 and medium 8 are formed, and needle-like monopole 6 links to each other with coaxial feeder inner wire 4, and metallic sheath 7 links to each other with coaxial feeder outer conductor 5.Fig. 3 (b) is the electrical dipole antenna structural representation, and it is by coaxial feeder inner wire 9, and coaxial feeder outer conductor 10 and medium 11 are formed.
Fig. 4, for the surface emissivity antenna structure view, this class antenna can be close to structure body surface curved surface microwave radiation.Fig. 4 (a) is the helix microstrip antenna, and it is made up of helix microstrip antenna and flexible media substrate.Fig. 4 (b) is a circular polarization microstrip antenna, and it is made up of circular polarization microstrip antenna 14 and flexible media substrate 15.Figure (a) can be combined into as scheming the display array configuration shown in (c) in the display mode with the element antenna of figure (b).
Fig. 5, be microwave fettling knife structural representation.It is a kind of electric small-size dipole, according to the shape of concrete damage location, can adopt corresponding shape.It is connected in hard coaxial inner conductor 17 by cutter shape jaw 16 and places 18 interior of hard coaxial outer conductors to form.The antenna of this version is mainly used in the repairing of special damage locations such as ditch, mortise, micropore.
Fig. 6, be traveling-wave field radiating antenna structural representation.The antenna form of Fig. 6 (a) is used for the Heating Repair that damage location is the plane.If when the construction end face of antenna is curved surface, can make the curved surface Heating Repair.
Fig. 6 (b) is made up of two semicircle tubes, and the damage location that is mainly used in tube outer surface or curved surface carries out Heating Repair.
Fig. 7, resonant cavity applicator antenna structure view.Formed by waveguide, logical filter section and resonant cavity, be used for the Heating Repair of plane damage location.
More than several radiating antennas have following characteristics:
1, radiating antenna is dimensionally much smaller than the microwave radiation wavelength, thereby volume is little, in light weight;
2, the shape of radiating antenna conforms to the local needs of accepting microwave radiation of damage, and it has concentrated spoke when needed
Penetrate the dual-use function of microwave energy and high-frequency electrocoagulation, cauterization effect obviously strengthens, but can be to normal machine on every side
Damage is caused at the tool position.
Claims (5)
1, a kind of damaged composite material in aircraft structure microwave fast repair technique and equipment, it is characterized in that being formed by microwave power source and microwave applicator, microwave power source is connected in axitron by controlled autotransformer secondary through rectifying circuit, automatic control circuit is connected in former limit of controlled autotransformer and the former limit of magnetron power source voltage transformer, and the magnetron power source voltage transformer provides the power supply of axitron; The microwave applicator that links to each other with the mouth of microwave power source links to each other with radiating antenna after being connected in coaxial feeder by adapter again.
2, damaged composite material in aircraft structure microwave fast repair technique according to claim 1 and equipment, it is characterized in that, the needle-like monopole antenna of tube chamber radiating antenna, its needle-like monopole links to each other with the coaxial feeder inner wire and places in the medium, and the outer needle-like monopole of medium one end is with metallic sheath and links to each other with the coaxial feeder outer conductor that is enclosed within the other end.
3, damaged composite material in aircraft structure microwave fast repair technique according to claim 1 and equipment is characterized in that, the coaxial feeder inner wire and the coaxial feeder outer conductor of the electrical dipole antenna of tube chamber radiating antenna all place medium.
4, damaged composite material in aircraft structure microwave fast repair technique according to claim 1 and equipment, it is characterized in that, the surface emissivity antenna has helix and circular polarization shape, place the flexible media substrate to be formed by microstrip antenna, its single element antenna can the display mode be combined into the array type antenna assemblies.
5, damaged composite material in aircraft structure microwave fast repair technique according to claim 1 and equipment is characterized in that, the microwave fettling knife is connected in hard coaxial line inside conductor by cutter shape jaw and places in the hard coaxial outer conductor and form.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN02112607A CN1361039A (en) | 2002-01-29 | 2002-01-29 | Fast repair technique and apparatus for damaged composite material in aircraft structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN02112607A CN1361039A (en) | 2002-01-29 | 2002-01-29 | Fast repair technique and apparatus for damaged composite material in aircraft structure |
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| Publication Number | Publication Date |
|---|---|
| CN1361039A true CN1361039A (en) | 2002-07-31 |
Family
ID=4742131
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|---|---|---|---|
| CN02112607A Pending CN1361039A (en) | 2002-01-29 | 2002-01-29 | Fast repair technique and apparatus for damaged composite material in aircraft structure |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100454744C (en) * | 2006-07-22 | 2009-01-21 | 梁伟国 | Microwave oven |
| CN102741846A (en) * | 2009-12-17 | 2012-10-17 | 空中客车运营简化股份公司 | Method for designing standardised repair kits for an aircraft fuselage |
| CN103950553A (en) * | 2014-04-25 | 2014-07-30 | 哈尔滨飞机工业集团有限责任公司 | Method for repairing countersunk crossed nest |
| CN104837231A (en) * | 2015-03-13 | 2015-08-12 | 南京航空航天大学 | Microwave heating restoring method and microwave heating restoring system |
| CN104903197A (en) * | 2013-01-11 | 2015-09-09 | 波音公司 | System and method for repairing composite aircraft structures |
| CN107054689A (en) * | 2015-10-27 | 2017-08-18 | 空中客车运营简化股份公司 | The repair method of Flight Vehicle Structure is repaired using deformable plate |
| CN110616046A (en) * | 2019-07-26 | 2019-12-27 | 中国航空工业集团公司济南特种结构研究所 | Method suitable for bonding large-size large-load radome tension-compression pads |
-
2002
- 2002-01-29 CN CN02112607A patent/CN1361039A/en active Pending
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100454744C (en) * | 2006-07-22 | 2009-01-21 | 梁伟国 | Microwave oven |
| CN102741846A (en) * | 2009-12-17 | 2012-10-17 | 空中客车运营简化股份公司 | Method for designing standardised repair kits for an aircraft fuselage |
| US9817452B2 (en) | 2013-01-11 | 2017-11-14 | The Boeing Company | System and method for thermal management guidance |
| CN104903197A (en) * | 2013-01-11 | 2015-09-09 | 波音公司 | System and method for repairing composite aircraft structures |
| US10216237B2 (en) | 2013-01-11 | 2019-02-26 | The Boeing Company | System and method for thermal management guidance |
| CN104903197B (en) * | 2013-01-11 | 2016-12-21 | 波音公司 | The system and method for repair composite material Flight Vehicle Structure |
| CN103950553A (en) * | 2014-04-25 | 2014-07-30 | 哈尔滨飞机工业集团有限责任公司 | Method for repairing countersunk crossed nest |
| CN103950553B (en) * | 2014-04-25 | 2016-02-24 | 哈尔滨飞机工业集团有限责任公司 | A kind ofly draw the repair method of nest to immersing oneself in |
| CN104837231A (en) * | 2015-03-13 | 2015-08-12 | 南京航空航天大学 | Microwave heating restoring method and microwave heating restoring system |
| CN104837231B (en) * | 2015-03-13 | 2016-11-23 | 南京航空航天大学 | Microwave heating restorative procedure and system |
| CN107054689A (en) * | 2015-10-27 | 2017-08-18 | 空中客车运营简化股份公司 | The repair method of Flight Vehicle Structure is repaired using deformable plate |
| CN107054689B (en) * | 2015-10-27 | 2021-10-01 | 空中客车运营简化股份公司 | Method for repairing aircraft structure using deformable sheets |
| CN110616046A (en) * | 2019-07-26 | 2019-12-27 | 中国航空工业集团公司济南特种结构研究所 | Method suitable for bonding large-size large-load radome tension-compression pads |
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