TECHNICAL FIELD

The disclosure generally relates to thermoplastic welding techniques. More particularly, the disclosure relates to a thermoplastic welding apparatus and method in which an induced magnetic field is oriented parallel to the plane of the composite parts being welded and concentrates uniform heating at the joint between the composite parts, preventing or minimizing heating of the parts.

BACKGROUND

Fiber-reinforced organic resin matrix composites have a high strength-to-weight ratio, a high stiffness-to-weight radio and desirable fatigue characteristics that make them increasingly popular in aerospace applications. Therefore, composite materials are increasingly being used in the fabrication of structural components for aircraft.

A variety of techniques are used to join composite structures in aerospace and other applications. These fastening techniques include mechanical fastening, adhesive bonding and thermoplastic welding. Thermoplastic welding has numerous advantages over the other fastening techniques including the ability to join thermoplastic composite components at high speeds and with minimum touch labor and little, if any, pretreatments. The welding interlayer (which includes a susceptor and surrounding thermoplastic resin either coating or sandwiching the susceptor) also can simultaneously take the place of shims which are required in mechanical fastening. Therefore, composite welding promises to be an affordable fastening technique.

In the thermoplastic welding of thermoplastic and thermoset composite parts, the susceptor between the composite parts is heated and, in turn, heats and melts the resin of the parts. The melted resin functions as a hot melt adhesive at the welding interlayer between the parts. Upon subsequent cooling, the resin solidifies and secures the composite parts to each other.

In thermoplastic welding, it is desirable to heat the welding interlayer between the composite parts as uniformly as possible. Thermal uniformity and repeatability, as well as the amount of time necessary to develop acceptable tooling and parameters to meet these acceptable thermal uniformity conditions, has been a primary impediment to utilizing induction welding of thermoplastic composites. Extensive experimentation in developing the parameters has been used in applications in which induction parameters and tooling with heat sinks have been used. Often, however, the thermoplastic welding process is not selected due to these thermal uniformity issues.

Therefore, a thermoplastic welding apparatus and method in which an induced magnetic field is oriented parallel to the plane of the composite parts being welded and concentrates uniform heating at the joint between the composite parts, preventing or minimizing heating of the parts, is needed.

SUMMARY

The disclosure is generally directed to a thermoplastic welding apparatus. An illustrative embodiment of the thermoplastic welding apparatus includes a thermoplastic welding tool, at least one tooling surface in the thermoplastic welding tool, a magnetic induction coil in the thermoplastic welding tool and generally encircling the at least one tooling surface and at least one smart susceptor in the thermoplastic welding tool at the at least one tooling surface. The magnetic induction coil is adapted to generate a magnetic flux field oriented generally parallel to a plane of the at least one smart susceptor.

In some embodiments, the thermoplastic welding apparatus may include a thermoplastic welding tool; at least one tooling space in the thermoplastic welding tool; at least one tooling surface in the at least one tooling space; a magnetic induction coil in the thermoplastic welding tool and generally encircling the at least one tooling surface; a first composite part on the tooling surface; at least one smart susceptor on the first composite part; and a second composite part on the at least one smart susceptor. The magnetic induction coil is adapted to generate a magnetic flux field oriented generally parallel to a plane of the at least one smart susceptor.

The disclosure is further generally directed to a thermoplastic welding method. An illustrative embodiment of the thermoplastic welding method includes providing first and second composite parts, placing a smart susceptor between the first and second composite parts and generating a magnetic flux field in parallel relationship to a plane of the smart susceptor.

Further embodiments of the disclosure may include:

A. A thermoplastic welding apparatus, comprising:

a thermoplastic welding tool;

at least one tooling space in said thermoplastic welding tool;

at least one tooling surface in said at least one tooling space; a magnetic induction coil in said thermoplastic welding tool and generally encircling said at least one tooling surface;

a first composite part on said tooling surface;

at least one smart susceptor on said first composite part;

a second composite part on said at least one smart susceptor; and said magnetic induction coil is adapted to generate a magnetic flux field oriented generally parallel to a plane of said at least one smart susceptor.

B. The apparatus of paragraph A wherein said at least one smart susceptor comprises molypermalloy.

C. The apparatus of paragraph A further comprising a ferromagnetic material embedded in said at least one tooling surface. D. The apparatus of paragraph A further comprising a non electrically-conductive material in said at least one tooling surface.

E. The apparatus of paragraph D wherein said non electrically-conductive material comprises an elastomeric material.

F. The apparatus of paragraph D further comprising a ferromagnetic material embedded in said at least one tooling surface next to said non electrically-conductive material. G. The apparatus of paragraph F wherein said ferromagnetic material is embedded in said at least one tooling surface on respective sides of said non electrically-conductive material.

H. The apparatus of paragraph F wherein said ferromagnetic material comprises ferrite powder. BRIEF DESCRIPTION OF THE ILLUSTRATIONS FIG. 1 is a cross-sectional view of an illustrative embodiment of the thermoplastic welding apparatus in exemplary application of the apparatus.

FIG. 2 is a cross-sectional view of a portion of an illustrative embodiment of the thermoplastic welding apparatus, more particularly illustrating parallel orientation of a magnetic flux field with a smart susceptor between adjacent composite parts in thermoplastic welding of the parts to each other.

FIG. 3 is an enlarged sectional view of the composite parts and the smart susceptor illustrated in FIG. 2.

FIG. 4 is a cross-sectional view of an illustrative embodiment of the thermoplastic welding apparatus in alternative application of the apparatus.

FIG. 5 is an enlarged sectional view of the composite parts and the smart susceptor illustrated in FIG. 4.

FIG. 6 is a flow diagram of an illustrative embodiment of a thermoplastic welding method.

FIG. 7 is a flow diagram of an aircraft production and service methodology.

FIG. 8 is a block diagram of an aircraft.

DETAILED DESCRIPTION

The following detailed description is merely exemplary in nature and is not intended to limit the described embodiments or the application and uses of the described embodiments. As used herein, the word "exemplary" or "illustrative" means "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" or "illustrative" is not necessarily to be construed as preferred or advantageous over other implementations. All of the implementations described below are exemplary implementations provided to enable persons skilled in the art to practice the disclosure and are not intended to limit the scope of the claims. Furthermore, there is no intention to be bound by any expressed or implied theory presented in the preceding technical field, background, brief summary or the following detailed description.

Referring initially to FIGS. 1-3, an illustrative embodiment of the thermoplastic welding apparatus is generally indicated by reference numeral 100. The thermoplastic welding apparatus 100 may include a thermoplastic welding tool 101. In some embodiments, the thermoplastic welding tool 101 may be a castable ceramic tool. Reinforcing rods 105, which may be fiberglass, may extend through the thermoplastic welding tool 101. The thermoplastic welding tool 101 may include a tooling space 106 having at least one tooling surface 103. Magnetic induction coils 102 may extend through the thermoplastic welding tool 101. The magnetic induction coils 102 may be disposed on both sides of the tooling space 106 and may generally surround or envelope the tooling surface 103.

A non electrically-conductive material 104 (FIG. 2) may be disposed generally beneath or adjacent to the tooling surface 103. In some embodiments, the non electrically- conductive material 104 may be an elastomeric material. A ferrite material such as ferrite powder 108, for example and without limitation, may be embedded in the thermoplastic welding tool 101 on at least one side and preferably, on respective sides of the non electrically-conductive material 104. The ferrite powder 108 may be distributed in a plane which is generally parallel to the plane of the smart susceptor 116 and the planes of the first composite part 112 and the second composite part 113, respectively.

In application of the thermoplastic welding apparatus 100, a first composite part 112 is placed on the tooling surface 103 in the tooling space 106 of the thermoplastic welding tool 101. A smart susceptor 116 is placed on the first composite part 112. The smart susceptor 116 may be an electrically-conductive, magnetic metal with high thermal conductivity such as molypermalloy, for example and without limitation. A second composite part 113 is placed on the smart susceptor 116. In some applications, tape 118 may be applied to the edges of the second composite part 113 to form a gas seal over the welding joint defined by the first composite part 112, the smart susceptor 116 and the second composite part 113. A vacuum is pulled on the tooling surface 103 and internal gas pressure 120 applies welding pressure against the second composite part 113, compressing the smart susceptor 116 between the first composite part 112 and the second composite part 113.

The magnetic induction coils 102 generate a magnetic flux field 122 which generally envelopes the first composite part 112 and the second composite part 113, as shown in FIG. 1. In some applications, the magnetic flux field 122 may be an 80kHz field with 10 amps excitation energy. Due to the high magnetic permeability of the smart susceptor 116, the magnetic flux lines 123 of the magnetic flux field 122 stream into the smart susceptor 116. The ferrite powder 108 focuses the magnetic flux field 122 and eliminates leakage of the magnetic flux field 122 into the first composite part 112 and the second composite part 113. Accordingly, the magnetic flux lines 123 of the magnetic flux field 122 follow the magnetic path of least resistance through the embedded ferrite powder 108 and the smart susceptor 116, as shown in FIG. 3. Consequently, the magnetic flux field 122 sustains a thermal reaction in the smart susceptor 116, heating the smart susceptor 116 to its Curie temperature point. The smart susceptor 116 heats and melts the resin at the welding interface between the first composite part 112 and the second composite part 113. Because the magnetic flux lines 123 of the magnetic flux field 122 encompass the entire part and are oriented parallel to the plane of the smart susceptor 116, minimal heating of the first composite part 112 and the second composite part 113 occurs and heating is focused, concentrated or localized to the welding interface between the first composite part 112 and the second composite part 113. The magnetic induction coils 102 are then turned off and the first composite part 112 and the second composite part 113 allowed to cool. The melted resin at the welding interface solidifies, forming an adhesive bond between the first composite part 112 and the second composite part 113. The composite structure which includes the first composite part 112 and the second composite part 113 may then be removed from the thermoplastic welding tool 101.

It will be appreciated by those skilled in the art that a 0.006" thick molypermalloy smart susceptor 116 is capable of being heated from room temperature to about 670 degrees F in about 3 minutes when exposed to a 80 kHz magnetic flux field 122 with an equilibrium temperature in the 670-680 degree F temperature range. A graphite/epoxy composite part 112, 113 does not heat noticeably when exposed to the same magnetic flux field 122. This characteristic enables thin, intrinsically-controlled susceptor materials to be used for thermoplastic composite welding to facilitate even or precise heating and repeatable processing.

Referring next to FIGS. 4 and 5, a cross-sectional view of an illustrative embodiment of the thermoplastic welding apparatus 100a in alternative application of the apparatus is shown. In application of the thermoplastic welding apparatus 100a, multiple smart susceptors 138 may be placed between a first composite part 134 and a second composite part 135 at selected intervals in the thermoplastic welding tool 101 depending on the desired locations of the welding interfaces between the parts. A non electrically-conductive material such as an elastomeric material 132, for example and without limitation, may extend adjacent to the first composite part 134 and the second composite part 135, respectively. A ferrite material 130 may be provided in the thermoplastic welding tool 101 generally on respective sides of the elastomeric material 132. The ferrite material 130 may be oriented in a plane which is generally parallel to the plane of the smart susceptor 108 and the planes of the first composite part 134 and the second composite part 135, respectively. Accordingly, upon energizing of the magnetic induction coils 102, the magnetic flux field 122 (FIG. 5) follows the path of least magnetic resistance through the ferrite material 130 and the smart susceptor 138. The smart susceptor 138 uniformly and selectively heats the welding interface between the first composite part 134 and the second composite part 135 without heating the first composite part 134 and the second composite part 135. Upon cooling, the melted resin at the welding interface solidifies and secures the parts to each other, after which the composite structure including the first composite part 134 an the second composite part 135 is removed from the thermoplastic welding tool 101.

Referring next to FIG. 6, a flow diagram 600 of an illustrative embodiment of a thermoplastic welding method is shown. In block 602, molded composite parts may be trimmed to net shape. In block 604, a smart susceptor may be placed between the composite parts which are to be joined via thermoplastic welding. In block 606, the composite parts and the susceptor may be placed in a thermoplastic welding tool. In block 608, magnetic induction coils of the tool may be arranged so that a magnetic flux field produced by the induction coils in the tool encompasses the entire part and is oriented parallel to the plane of the smart susceptor and parallel to the planes of the composite parts being joined. In block 610, tape may be placed around the joint edges of the composite parts and a vacuum may be pulled at the joint. In block 612, tooling force may be applied against the composite parts to supply welding pressure. In some embodiments, the tooling force may be a pressurized gas. In block 614, the induction coil may be energized. In block 616, polymeric material at the welding interface between the composite parts may melt to form the weld. In block 618, power to the coil may be terminated to cool and solidify the joint and the composite structure may be removed from the tool.

Referring next to FIGS. 7 and 8, embodiments of the disclosure may be used in the context of an aircraft manufacturing and service method 78 as shown in FIG. 7 and an aircraft 94 as shown in FIG. 8. During pre-production, exemplary method 78 may include specification and design 80 of the aircraft 94 and material procurement 82. During production, component and subassembly manufacturing 84 and system integration 86 of the aircraft 94 takes place. Thereafter, the aircraft 94 may go through certification and delivery 88 in order to be placed in service 90. While in service by a customer, the aircraft 94 may be scheduled for routine maintenance and service 92 (which may also include modification, reconfiguration, refurbishment, and so on).

Each of the processes of method 78 may be performed or carried out by a system integrator, a third party, and/or an operator (e.g., a customer). For the purposes of this description, a system integrator may include without limitation any number of aircraft manufacturers and major-system subcontractors; a third party may include without limitation any number of vendors, subcontractors, and suppliers; and an operator may be an airline, leasing company, military entity, service organization, and so on.

As shown in FIG. 8, the aircraft 94 produced by exemplary method 78 may include an airframe 98 with a plurality of systems 96 and an interior 100. Examples of high-level systems 96 include one or more of a propulsion system 102, an electrical system 104, a hydraulic system 106, and an environmental system 108. Any number of other systems may be included. Although an aerospace example is shown, the principles of the invention may be applied to other industries, such as the automotive industry.

The apparatus embodied herein may be employed during any one or more of the stages of the production and service method 78. For example, components or subassemblies corresponding to production process 84 may be fabricated or manufactured in a manner similar to components or subassemblies produced while the aircraft 94 is in service. Also one or more apparatus embodiments may be utilized during the production stages 84 and 86, for example, by substantially expediting assembly of or reducing the cost of an aircraft 94. Similarly, one or more apparatus embodiments may be utilized while the aircraft 94 is in service, for example and without limitation, to maintenance and service 92.

Although the embodiments of this disclosure have been described with respect to certain exemplary embodiments, it is to be understood that the specific embodiments are for purposes of illustration and not limitation, as other variations will occur to those of skill in the art.