DESC:FORM 2

THE PATENTS ACT, 1970
(39 of 1970)
&
THE PATENT RULES, 2003

COMPLETE SPECIFICATION
(See Section 10 and Rule 13)

Title of invention:
A SYSTEM AND METHOD FOR FABRICATING WING INBOARD PANELS AND BRACKETS ON MISSILE MOTOR CASING

Applicant:
BEML Limited
A company Incorporated in India under the Companies Act, 1956
Having Address As:
BEML Soudha, 23/1, 4th Main,
Sampangirama Nagar, Bengaluru - 560 027,
Karnataka, India

The following specification particularly describes the invention and the manner in which it is to be performed.
CROSS-REFERENCE TO RELATED APPLICATIONS AND PRIORITY
[001] The present invention claims priority from Indian patent application numbered IN 202241047282 filed on 19th August, 2022.

FIELD OF THE INVENTION
[002] The present subject matter described herein generally relates to a system and method for fabricating wing inboard panels and brackets on missile motor casing, and more specifically for a system and method for fabricating wing inboard panels and brackets on missile motor casing using TIG welding by CNC special purpose machine.
BACKGROUND
[003] The motor casing of a missile is a thin walled flow formed tube of thickness 1.3mm made up of 18% Ni Maraging steel. The wing inboard panels, launch shoes and wire tunnel brackets are welded on the circumference of the tube at various locations precisely as per the design requirements. The orthogonality of 90°±30' and CANT angle of 45°±15' defines the position of wings and also defines the trajectory of missile system. The position of launch shoes defines the proper ejection of missile from the canister.
[004] The major challenge in this process is to weld the components on the thin walled tube to achieve the required levels of accuracy with minimum weld distortion. The weld penetration should be less than 25% of the wall thickness.
[005] When mechanical welding fixtures are used for fabrication, achieving repeatability and accuracy is hard. During assembling and disassembling of the mechanical parts, due to wear and tear the dimensional accuracy varies.
[006] Hence to overcome the aforesaid drawbacks there is a requirement to provide a system and method to fabricate wing inboard panels and brackets on a thin walled missile motor casing to achieve the required level of accuracy.
OBJECTS OF THE INVENTION
[007] Main object of the present disclosure is to provide a system and method for fabricating wing inboard panels and brackets on missile motor casing to achieve the required level of accuracy.
[008] Another object of the present disclosure is to provide a system and method for fabricating wing inboard panels and brackets on missile motor casing using copper backup with Argon purging to reduce welding distortion.
[009] Yet another object of the present disclosure is to provide a system and method for fabricating wing inboard panels and brackets on missile motor casing to improve productivity.
[0010] Another object of the present disclosure is to provide a system and method for fabricating wing inboard panels and brackets on missile motor casing to have better control over weld fusion depth thus reducing welding penetration.
[0011] Yet another object of the present disclosure is to provide a system and method for fabricating wing inboard panels and brackets on missile motor casing to eliminate inner surface oxidation by creating inert atmosphere.
[0012] Another object of the present disclosure is to provide a system and method for fabricating wing inboard panels and brackets on missile motor casing to optimize production cycle time.
[0013] Yet another object of the present disclosure is to provide a system and method for fabricating wing inboard panels and brackets on missile motor casing to achieve repeatability.
[0014] Yet another object of the present disclosure is to provide a system and method for fabricating wing inboard panels and brackets on missile motor casing which is compact, cost effective and easy to implement.
SUMMARY
[0015] Before the present system is described, it is to be understood that this application is not limited to a particular machine, device or system, as there can be multiple possible embodiments that are not expressly illustrated in the present disclosures. It is also to be understood that the terminology used in the description is for the purpose of describing the particular versions or embodiments only, and is not intended to limit the scope of the present application. This summary is provided to introduce aspects related to a system and method for fabricating wing inboard panels and brackets on missile motor casing, and the aspects are further elaborated below in the detailed description. This summary is not intended to identify essential features of the proposed subject matter nor is it intended for use in determining or limiting the scope of the proposed subject matter.
[0016] The present subject matter discloses a system for fabricating wing inboard panels and brackets on missile motor casing comprising a moving column for mounting plurality of components on a motor casing for welding. A head stock and a tailstock to support and align the motor casing. A copper backup apparatus for supporting the said motor casing welded area from the inner surface. Plurality of servo motors to control the movements of the moving column and the head stock. A pneumatic system for operating the tailstock, and actuating the copper backup apparatus.
[0017] A method for fabricating wing inboard panels and brackets on missile motor casing comprising indexing of a motor casing by a servo motor. Plurality of components of the motor casing are aligned serially between a headstock and a tail stock. A copper backup apparatus is supported from the inner surface of the plurality of components of the motor casing by a pneumatic system. The central axis of rotation of the motor casing and a spindle is aligned. Both the ends of the plurality of components are clamped on the motor casing. A wing inboard panel is mounted at appropriate position on the motor casing using a moving column through attachments. The flow of argon gas is ensured in the copper backup apparatus. The positioned plurality of wing inboard panels, plurality of wire tunnel brackets, and plurality of launch shoes is welded on the motor casing in sequence. The welded joints of the motor casing assembly are inspected.
STATEMENT OF INVENTION
[0018] The present subject matter discloses, a system to fabricate wing inboard panels and brackets on missile motor casing comprising a moving column for mounting plurality of components on a motor casing for welding. A head stock and a tailstock to support and align the motor casing. A copper backup apparatus for supporting the said motor casing from the inner surface. Plurality of servo motors to control the movements of the moving column and the head stock. A pneumatic system for operating the tailstock, and actuating the copper backup apparatus.
[0019] In an embodiment, the copper backup apparatus is operated pneumatically.
[0020] In an embodiment, the said pneumatically operated with a noble gas which is an argon gas.
[0021] In an embodiment, the plurality of components are plurality of wing inboard panels, plurality of wire tunnel brackets, plurality of launch shoes, a missile motor casing and a pressure vessel.
[0022] In an embodiment, the copper backup apparatus is supported between the headstock and the tailstock.
[0023] In an embodiment, the copper backup apparatus is provided with plurality of holes.
[0024] In an embodiment, the system is a computerized numerically controlled (CNC) machine.
[0025] In another embodiment, a method for fabricating wing inboard panels and brackets on missile motor casing comprising indexing of a motor casing by a servo motor. Plurality of components of the motor casing are aligned serially between a headstock and a tail stock. A copper backup apparatus is supported from the inner surface of the plurality of components of the motor casing by a pneumatic system. The central axis of rotation of the motor casing and a spindle is aligned. Both the ends of the plurality of components is clamped on the motor casing. A wing inboard panel is mounted at appropriate position on the motor casing using a moving column through attachments. The flow of argon gas is ensured in the copper backup apparatus. The positioned plurality of wing inboard panels, plurality of wire tunnel brackets, and plurality of launch shoes is welded on the motor casing. The welded joints of the motor casing assembly are inspected.
BRIEF DESCRIPTION OF THE DRAWINGS
[0026] The foregoing summary, as well as the following detailed description of embodiments, is better understood when read in conjunction with the appended drawings. For the purpose of illustrating the disclosure, there is shown in the present document example constructions of the disclosure, however, the disclosure is not limited to the specific methods and device disclosed in the document and the drawing. The detailed description is described with reference to the following accompanying figures.
[0027] Figure 1 illustrates an isometric view of a system for fabricating wing inboard panels and brackets on missile motor casing, in accordance with an embodiment of the present subject matter.
[0028] Figure 2 illustrates an isometric view of the welded assembly of missile motor casing of the system for fabricating wing inboard panels and brackets on missile motor casing, in accordance with an embodiment of the present subject matter.
[0029] Figure 3 illustrates an enlarged view of the welded wing inboard panel structure on missile motor casing of the system for fabricating wing inboard panels and brackets on missile motor casing, in accordance with an embodiment of the present subject matter.
[0030] Figure 4 illustrates a cross-sectional view of missile motor casing of the system for fabricating wing inboard panels and brackets on missile motor casing, in accordance with an embodiment of the present subject matter.
[0031] Figure 5 illustrates a flowchart of a method for fabricating wing inboard panels and brackets on missile motor casing, in accordance with an embodiment of the present subject matter.
[0032] The figures depict various embodiments of the present disclosure for purposes of illustration only. One skilled in the art will readily recognize from the following discussion that alternative embodiments of the structures illustrated herein may be employed without departing from the principles of the disclosure described herein.
DETAILED DESCRIPTION OF INVENTION
[0033] Some embodiments of this disclosure, illustrating all its features, will now be discussed in detail. The words "comprising", “having”, and "including," and other forms thereof, are intended to be equivalent in meaning and be open ended in that an item or items following any one of these words is not meant to be an exhaustive listing of such item or items, or meant to be limited to only the listed item or items. It must also be noted that as used herein and in the appended claims, the singular forms "a," "an," and "the" include plural references unless the context clearly dictates otherwise. Although any devices and methods similar or equivalent to those described herein can be used in the practice or testing of embodiments of the present disclosure, the exemplary, devices and methods are now described. The disclosed embodiments are merely exemplary of the disclosure, which may be embodied in various forms.
[0034] Various modifications to the embodiment will be readily apparent to those skilled in the art and the generic principles herein may be applied to other embodiments. However, one of ordinary skill in the art will readily recognize that the present disclosure is not intended to be limited to the embodiments illustrated, but is to be accorded the widest scope consistent with the principles and features described herein.
[0035] The present subject matter discloses a system (100) and method (200) for fabricating wing inboard panels and brackets on missile motor casing.
[0036] Now referring to figure 1, an isometric view of a system (100) for fabricating wing inboard panels and brackets on missile motor casing is disclosed. The system (100) comprises a special purpose computerized numerically controlled (CNC) machine (120) to fabricate the missile motor casing assembly (110). The computerized numerically controlled (CNC) machine (120) comprises of a heavy bed (not shown in figure), a moving column (104), a head stock (102), a tailstock (108), a copper backup apparatus (106), plurality of servo motors (not shown in figure) and a pneumatic system (not shown in figure). The moving column (104) is provided for mounting plurality of components on the motor casing (116) for welding. The plurality of components are plurality of wing inboard panels (118), plurality of wire tunnel brackets, plurality of launch shoes, a missile motor casing (116) and a pressure vessel. The head stock (102) and the tailstock (108) are provided for supporting and aligning the motor casing (116). The movement of the moving column (104) and the head stock (102) are controlled by the servo motor. The copper backup apparatus (106) is provided for supporting the said motor casing (116) from inner surface. The copper backup apparatus (106) is supported between the headstock (102) and the tailstock (108). The tailstock (108) is adjusted and/or operated by the pneumatic system. The copper backup apparatus (106) is engaged and disengaged by the pneumatic system. Further, the copper backup apparatus (106) is operated pneumatically with a noble gas such as an argon gas through the plurality of holes provided on the copper backup apparatus (106).
[0037] Now referring to figure 2 and figure 3, figure 2 relates to an isometric view of the welded assembly (110) of missile motor casing and figure 3 relates to an enlarged view of the welded wing inboard panel structure (110) on missile motor casing. The motor casing assembly (110) comprises of the motor casing (116) with welded wing inboard panel (118). The welding is done using TIG welding by the CNC special purpose machine (120).
[0038] Now referring to figure 4, a cross-sectional view of missile motor casing (110) of the system for fabricating wing inboard panels and brackets on missile motor casing by the CNC machine (120) is shown. The concentricity between all the ends are ensured.
[0039] Now referring to figure 5, a method (200) for fabricating wing inboard panels and brackets on missile motor casing is shown. In step 202, indexing of the motor casing (116) by a servo motor of the CNC machine (120) is done. In step 204, plurality of components of the motor casing (116) are aligned serially between the head stock (102) and the tail stock (108). In step 206, the copper backup apparatus (106) is clamped from the inner surface of the plurality of components of the motor casing (116) by the pneumatic system. In step 208, the central axis of rotation of the motor casing (116) and a spindle (not shown in figure) is aligned. In step 210, both the ends of the plurality of components are clamped on the motor casing (116). In step 212, a wing inboard panel (118) is mounted at appropriate position on the motor casing (116) using the moving column (104) through attachments. In step 214, the flow of noble gas in the copper backup apparatus (106) is ensured. After proper butting of wing inboard panel (118) is ensured, welding is done in step 216. Further, the positioned plurality of wing inboard panels (118), plurality of wire tunnel brackets, and plurality of launch shoes are welded on the motor casing (116). Similarly all the four wing inboard panels (118) are positioned as per the requirement and welded as shown in figure 2 and 3. After completion of the wing inboard panel (118) welding, a wire tunnel brackets are welded using suitable attachment by moving the moving column (104) to the appropriate locations. The launch shoes are similarly welded as per the requirements. In step 218, the welded joints of the motor casing assembly (110) are inspected.
[0040] The fabricating method (200) and system (100) of the present subject matter includes the CNC machine (120) which is servo controlled and attachments for fixing the wing inboard panels, the launch shoes and the wire tunnel brackets.
[0041] The present subject matter discloses the CNC controlled special purpose fixture, which locates the components accurately in its position as per the provided input. This ensures all the components are welded on to the missile motor casing assembly (110) with accuracy, minimum cycle time and can be repeated to increase productivity. As the inner surface of the motor casing (116) with copper backup (106) is purged by argon, this will enable to have better control over weld fusion depth, reduce weld distortion and eliminate the oxidation of the inner surface of the motor casing due to inert atmosphere.
[0042] The fabricating method (200) of wing inboard panels (118) and brackets on missile motor casing assembly (110) is done to achieve the required level of accuracy, reduce welding distortion and welding penetration as shown in figure 4. Different types of missile motor casings and pressure vessels can be fabricated using this fabricating method (200) and system (100).
[0043] Exemplary embodiments discussed above may provide certain advantages. Though not required to practice aspects of the disclosure, these advantages may include the following.
[0044] Some embodiments of the subject matter enable to provide the system and method for fabricating wing inboard panels and brackets on missile motor casing to achieve the required level of accuracy.
[0045] Some embodiments of the subject matter enable to provide the system and method for fabricating wing inboard panels and brackets on missile motor casing using copper backup with Argon purging to reduce welding distortion.
[0046] Some embodiments of the subject matter enable to provide the system and method for fabricating wing inboard panels and brackets on missile motor casing to improve productivity.
[0047] Some embodiments of the subject matter enable to provide the system and method for fabricating wing inboard panels and brackets on missile motor casing to have better control over weld fusion depth thus reducing welding penetration.
[0048] Some embodiments of the subject matter enable to provide the system and method for fabricating wing inboard panels and brackets on missile motor casing to eliminate inner surface oxidation by creating inert atmosphere.
[0049] Some embodiments of the subject matter enable to provide the system and method for fabricating wing inboard panels and brackets on missile motor casing to optimize production cycle time.
[0050] Some embodiments of the subject matter enable to the system and method for fabricating wing inboard panels and brackets on missile motor casing to achieve repeatability.
[0051] Some embodiments of the subject matter enable to provide the system and method for fabricating wing inboard panels and brackets on missile motor casing which is compact, cost effective and easy to implement.
[0052] Following is a list of elements and reference numerals used to explain various embodiments of the present subject matter.
Reference Numeral Element Description
100 system
102 Head Stock
104 Moving Column
106 Copper Backup apparatus
108 Tail Stock
110 Missile Motor Casing Assembly
116 Motor Casing
118 Wing Inboard Panel
120 CNC Machine

Equivalents
[0053] With respect to the use of substantially any plural and/or singular terms herein, those having skill in the art can translate from the plural to the singular and/or from the singular to the plural as is appropriate to the context and/or application. The various singular/plural permutations may be expressly set forth herein for sake of clarity.
[0054] It will be understood by those within the art that, in general, terms used herein, and especially in the appended claims (e.g., bodies of the appended claims) are generally intended as "open" terms (e.g., the term "including" should be interpreted as "including but not limited to," the term "having" should be interpreted as "having at least," the term "includes" should be interpreted as "includes but is not limited to," etc.). It will be further understood by those within the art that if a specific number of an introduced claim recitation is intended, such an intent will be explicitly recited in the claim, and in the absence of such recitation no such intent is present. For example, as an aid to understanding, the following appended claims may contain usage of the introductory phrases "at least one" and "one or more" to introduce claim recitations. However, the use of such phrases should not be construed to imply that the introduction of a claim recitation by the indefinite articles "a" or "an" limits any particular claim containing such introduced claim recitation to inventions containing only one such recitation, even when the same claim includes the introductory phrases "one or more" or "at least one" and indefinite articles such as "a" or "an" (e.g., "a" and/or "an" should typically be interpreted to mean "at least one" or "one or more"); the same holds true for the use of definite articles used to introduce claim recitations. In addition, even if a specific number of an introduced claim recitation is explicitly recited, those skilled in the art will recognize that such recitation should typically be interpreted to mean at least the recited number (e.g., the bare recitation of "two recitations," without other modifiers, typically means at least two recitations, or two or more recitations). Furthermore, in those instances where a convention analogous to "at least one of A, B, and C, etc." is used, in general such a construction is intended in the sense one having skill in the art would understand the convention (e.g., "a system having at least one of A, B, and C" would include but not be limited to systems that have A alone, B alone, C alone, A and B together, A and C together, B and C together, and/or A, B, and C together, etc.). In those instances, where a convention analogous to "at least one of A, B, or C, etc." is used, in general such a construction is intended in the sense one having skill in the art would understand the convention (e.g., "a system having at least one of A, B, or C" would include but not be limited to systems that have A alone, B alone, C alone, A and B together, A and C together, B and C together, and/or A, B, and C together, etc.). It will be further understood by those within the art that virtually any disjunctive word and/or phrase presenting two or more alternative terms, whether in the description, claims, or drawings, should be understood to contemplate the possibilities of including one of the terms, either of the terms, or both terms. For example, the phrase "A or B" will be understood to include the possibilities of "A" or "B" or "A and B."
[0055] Although implementations for a system and method for fabricating wing inboard panels and brackets on missile motor casing have been described in language specific to structural features and/or methods, it is to be understood that the appended claims are not necessarily limited to the specific features described. Rather, the specific features are disclosed as examples of implementation for the system and method for fabricating wing inboard panels and brackets on missile motor casing.

,CLAIMS:FORM 2

THE PATENTS ACT, 1970
(39 of 1970)
&
THE PATENT RULES, 2003

COMPLETE SPECIFICATION
(See Section 10 and Rule 13)

Title of invention:
A SYSTEM AND METHOD FOR FABRICATING WING INBOARD PANELS AND BRACKETS ON MISSILE MOTOR CASING

Applicant:
BEML Limited
A company Incorporated in India under the Companies Act, 1956
Having Address As:
BEML Soudha, 23/1, 4th Main,
Sampangirama Nagar, Bengaluru - 560 027,
Karnataka, India

The following specification particularly describes the invention and the manner in which it is to be performed.
CROSS-REFERENCE TO RELATED APPLICATIONS AND PRIORITY
[001] The present invention claims priority from Indian patent application numbered IN 202241047282 filed on 19th August, 2022.

FIELD OF THE INVENTION
[002] The present subject matter described herein generally relates to a system and method for fabricating wing inboard panels and brackets on missile motor casing, and more specifically for a system and method for fabricating wing inboard panels and brackets on missile motor casing using TIG welding by CNC special purpose machine.
BACKGROUND
[003] The motor casing of a missile is a thin walled flow formed tube of thickness 1.3mm made up of 18% Ni Maraging steel. The wing inboard panels, launch shoes and wire tunnel brackets are welded on the circumference of the tube at various locations precisely as per the design requirements. The orthogonality of 90°±30' and CANT angle of 45°±15' defines the position of wings and also defines the trajectory of missile system. The position of launch shoes defines the proper ejection of missile from the canister.
[004] The major challenge in this process is to weld the components on the thin walled tube to achieve the required levels of accuracy with minimum weld distortion. The weld penetration should be less than 25% of the wall thickness.
[005] When mechanical welding fixtures are used for fabrication, achieving repeatability and accuracy is hard. During assembling and disassembling of the mechanical parts, due to wear and tear the dimensional accuracy varies.
[006] Hence to overcome the aforesaid drawbacks there is a requirement to provide a system and method to fabricate wing inboard panels and brackets on a thin walled missile motor casing to achieve the required level of accuracy.
OBJECTS OF THE INVENTION
[007] Main object of the present disclosure is to provide a system and method for fabricating wing inboard panels and brackets on missile motor casing to achieve the required level of accuracy.
[008] Another object of the present disclosure is to provide a system and method for fabricating wing inboard panels and brackets on missile motor casing using copper backup with Argon purging to reduce welding distortion.
[009] Yet another object of the present disclosure is to provide a system and method for fabricating wing inboard panels and brackets on missile motor casing to improve productivity.
[0010] Another object of the present disclosure is to provide a system and method for fabricating wing inboard panels and brackets on missile motor casing to have better control over weld fusion depth thus reducing welding penetration.
[0011] Yet another object of the present disclosure is to provide a system and method for fabricating wing inboard panels and brackets on missile motor casing to eliminate inner surface oxidation by creating inert atmosphere.
[0012] Another object of the present disclosure is to provide a system and method for fabricating wing inboard panels and brackets on missile motor casing to optimize production cycle time.
[0013] Yet another object of the present disclosure is to provide a system and method for fabricating wing inboard panels and brackets on missile motor casing to achieve repeatability.
[0014] Yet another object of the present disclosure is to provide a system and method for fabricating wing inboard panels and brackets on missile motor casing which is compact, cost effective and easy to implement.
SUMMARY
[0015] Before the present system is described, it is to be understood that this application is not limited to a particular machine, device or system, as there can be multiple possible embodiments that are not expressly illustrated in the present disclosures. It is also to be understood that the terminology used in the description is for the purpose of describing the particular versions or embodiments only, and is not intended to limit the scope of the present application. This summary is provided to introduce aspects related to a system and method for fabricating wing inboard panels and brackets on missile motor casing, and the aspects are further elaborated below in the detailed description. This summary is not intended to identify essential features of the proposed subject matter nor is it intended for use in determining or limiting the scope of the proposed subject matter.
[0016] The present subject matter discloses a system for fabricating wing inboard panels and brackets on missile motor casing comprising a moving column for mounting plurality of components on a motor casing for welding. A head stock and a tailstock to support and align the motor casing. A copper backup apparatus for supporting the said motor casing welded area from the inner surface. Plurality of servo motors to control the movements of the moving column and the head stock. A pneumatic system for operating the tailstock, and actuating the copper backup apparatus.
[0017] A method for fabricating wing inboard panels and brackets on missile motor casing comprising indexing of a motor casing by a servo motor. Plurality of components of the motor casing are aligned serially between a headstock and a tail stock. A copper backup apparatus is supported from the inner surface of the plurality of components of the motor casing by a pneumatic system. The central axis of rotation of the motor casing and a spindle is aligned. Both the ends of the plurality of components are clamped on the motor casing. A wing inboard panel is mounted at appropriate position on the motor casing using a moving column through attachments. The flow of argon gas is ensured in the copper backup apparatus. The positioned plurality of wing inboard panels, plurality of wire tunnel brackets, and plurality of launch shoes is welded on the motor casing in sequence. The welded joints of the motor casing assembly are inspected.
STATEMENT OF INVENTION
[0018] The present subject matter discloses, a system to fabricate wing inboard panels and brackets on missile motor casing comprising a moving column for mounting plurality of components on a motor casing for welding. A head stock and a tailstock to support and align the motor casing. A copper backup apparatus for supporting the said motor casing from the inner surface. Plurality of servo motors to control the movements of the moving column and the head stock. A pneumatic system for operating the tailstock, and actuating the copper backup apparatus.
[0019] In an embodiment, the copper backup apparatus is operated pneumatically.
[0020] In an embodiment, the said pneumatically operated with a noble gas which is an argon gas.
[0021] In an embodiment, the plurality of components are plurality of wing inboard panels, plurality of wire tunnel brackets, plurality of launch shoes, a missile motor casing and a pressure vessel.
[0022] In an embodiment, the copper backup apparatus is supported between the headstock and the tailstock.
[0023] In an embodiment, the copper backup apparatus is provided with plurality of holes.
[0024] In an embodiment, the system is a computerized numerically controlled (CNC) machine.
[0025] In another embodiment, a method for fabricating wing inboard panels and brackets on missile motor casing comprising indexing of a motor casing by a servo motor. Plurality of components of the motor casing are aligned serially between a headstock and a tail stock. A copper backup apparatus is supported from the inner surface of the plurality of components of the motor casing by a pneumatic system. The central axis of rotation of the motor casing and a spindle is aligned. Both the ends of the plurality of components is clamped on the motor casing. A wing inboard panel is mounted at appropriate position on the motor casing using a moving column through attachments. The flow of argon gas is ensured in the copper backup apparatus. The positioned plurality of wing inboard panels, plurality of wire tunnel brackets, and plurality of launch shoes is welded on the motor casing. The welded joints of the motor casing assembly are inspected.
BRIEF DESCRIPTION OF THE DRAWINGS
[0026] The foregoing summary, as well as the following detailed description of embodiments, is better understood when read in conjunction with the appended drawings. For the purpose of illustrating the disclosure, there is shown in the present document example constructions of the disclosure, however, the disclosure is not limited to the specific methods and device disclosed in the document and the drawing. The detailed description is described with reference to the following accompanying figures.
[0027] Figure 1 illustrates an isometric view of a system for fabricating wing inboard panels and brackets on missile motor casing, in accordance with an embodiment of the present subject matter.
[0028] Figure 2 illustrates an isometric view of the welded assembly of missile motor casing of the system for fabricating wing inboard panels and brackets on missile motor casing, in accordance with an embodiment of the present subject matter.
[0029] Figure 3 illustrates an enlarged view of the welded wing inboard panel structure on missile motor casing of the system for fabricating wing inboard panels and brackets on missile motor casing, in accordance with an embodiment of the present subject matter.
[0030] Figure 4 illustrates a cross-sectional view of missile motor casing of the system for fabricating wing inboard panels and brackets on missile motor casing, in accordance with an embodiment of the present subject matter.
[0031] Figure 5 illustrates a flowchart of a method for fabricating wing inboard panels and brackets on missile motor casing, in accordance with an embodiment of the present subject matter.
[0032] The figures depict various embodiments of the present disclosure for purposes of illustration only. One skilled in the art will readily recognize from the following discussion that alternative embodiments of the structures illustrated herein may be employed without departing from the principles of the disclosure described herein.
DETAILED DESCRIPTION OF INVENTION
[0033] Some embodiments of this disclosure, illustrating all its features, will now be discussed in detail. The words "comprising", “having”, and "including," and other forms thereof, are intended to be equivalent in meaning and be open ended in that an item or items following any one of these words is not meant to be an exhaustive listing of such item or items, or meant to be limited to only the listed item or items. It must also be noted that as used herein and in the appended claims, the singular forms "a," "an," and "the" include plural references unless the context clearly dictates otherwise. Although any devices and methods similar or equivalent to those described herein can be used in the practice or testing of embodiments of the present disclosure, the exemplary, devices and methods are now described. The disclosed embodiments are merely exemplary of the disclosure, which may be embodied in various forms.
[0034] Various modifications to the embodiment will be readily apparent to those skilled in the art and the generic principles herein may be applied to other embodiments. However, one of ordinary skill in the art will readily recognize that the present disclosure is not intended to be limited to the embodiments illustrated, but is to be accorded the widest scope consistent with the principles and features described herein.
[0035] The present subject matter discloses a system (100) and method (200) for fabricating wing inboard panels and brackets on missile motor casing.
[0036] Now referring to figure 1, an isometric view of a system (100) for fabricating wing inboard panels and brackets on missile motor casing is disclosed. The system (100) comprises a special purpose computerized numerically controlled (CNC) machine (120) to fabricate the missile motor casing assembly (110). The computerized numerically controlled (CNC) machine (120) comprises of a heavy bed (not shown in figure), a moving column (104), a head stock (102), a tailstock (108), a copper backup apparatus (106), plurality of servo motors (not shown in figure) and a pneumatic system (not shown in figure). The moving column (104) is provided for mounting plurality of components on the motor casing (116) for welding. The plurality of components are plurality of wing inboard panels (118), plurality of wire tunnel brackets, plurality of launch shoes, a missile motor casing (116) and a pressure vessel. The head stock (102) and the tailstock (108) are provided for supporting and aligning the motor casing (116). The movement of the moving column (104) and the head stock (102) are controlled by the servo motor. The copper backup apparatus (106) is provided for supporting the said motor casing (116) from inner surface. The copper backup apparatus (106) is supported between the headstock (102) and the tailstock (108). The tailstock (108) is adjusted and/or operated by the pneumatic system. The copper backup apparatus (106) is engaged and disengaged by the pneumatic system. Further, the copper backup apparatus (106) is operated pneumatically with a noble gas such as an argon gas through the plurality of holes provided on the copper backup apparatus (106).
[0037] Now referring to figure 2 and figure 3, figure 2 relates to an isometric view of the welded assembly (110) of missile motor casing and figure 3 relates to an enlarged view of the welded wing inboard panel structure (110) on missile motor casing. The motor casing assembly (110) comprises of the motor casing (116) with welded wing inboard panel (118). The welding is done using TIG welding by the CNC special purpose machine (120).
[0038] Now referring to figure 4, a cross-sectional view of missile motor casing (110) of the system for fabricating wing inboard panels and brackets on missile motor casing by the CNC machine (120) is shown. The concentricity between all the ends are ensured.
[0039] Now referring to figure 5, a method (200) for fabricating wing inboard panels and brackets on missile motor casing is shown. In step 202, indexing of the motor casing (116) by a servo motor of the CNC machine (120) is done. In step 204, plurality of components of the motor casing (116) are aligned serially between the head stock (102) and the tail stock (108). In step 206, the copper backup apparatus (106) is clamped from the inner surface of the plurality of components of the motor casing (116) by the pneumatic system. In step 208, the central axis of rotation of the motor casing (116) and a spindle (not shown in figure) is aligned. In step 210, both the ends of the plurality of components are clamped on the motor casing (116). In step 212, a wing inboard panel (118) is mounted at appropriate position on the motor casing (116) using the moving column (104) through attachments. In step 214, the flow of noble gas in the copper backup apparatus (106) is ensured. After proper butting of wing inboard panel (118) is ensured, welding is done in step 216. Further, the positioned plurality of wing inboard panels (118), plurality of wire tunnel brackets, and plurality of launch shoes are welded on the motor casing (116). Similarly all the four wing inboard panels (118) are positioned as per the requirement and welded as shown in figure 2 and 3. After completion of the wing inboard panel (118) welding, a wire tunnel brackets are welded using suitable attachment by moving the moving column (104) to the appropriate locations. The launch shoes are similarly welded as per the requirements. In step 218, the welded joints of the motor casing assembly (110) are inspected.
[0040] The fabricating method (200) and system (100) of the present subject matter includes the CNC machine (120) which is servo controlled and attachments for fixing the wing inboard panels, the launch shoes and the wire tunnel brackets.
[0041] The present subject matter discloses the CNC controlled special purpose fixture, which locates the components accurately in its position as per the provided input. This ensures all the components are welded on to the missile motor casing assembly (110) with accuracy, minimum cycle time and can be repeated to increase productivity. As the inner surface of the motor casing (116) with copper backup (106) is purged by argon, this will enable to have better control over weld fusion depth, reduce weld distortion and eliminate the oxidation of the inner surface of the motor casing due to inert atmosphere.
[0042] The fabricating method (200) of wing inboard panels (118) and brackets on missile motor casing assembly (110) is done to achieve the required level of accuracy, reduce welding distortion and welding penetration as shown in figure 4. Different types of missile motor casings and pressure vessels can be fabricated using this fabricating method (200) and system (100).
[0043] Exemplary embodiments discussed above may provide certain advantages. Though not required to practice aspects of the disclosure, these advantages may include the following.
[0044] Some embodiments of the subject matter enable to provide the system and method for fabricating wing inboard panels and brackets on missile motor casing to achieve the required level of accuracy.
[0045] Some embodiments of the subject matter enable to provide the system and method for fabricating wing inboard panels and brackets on missile motor casing using copper backup with Argon purging to reduce welding distortion.
[0046] Some embodiments of the subject matter enable to provide the system and method for fabricating wing inboard panels and brackets on missile motor casing to improve productivity.
[0047] Some embodiments of the subject matter enable to provide the system and method for fabricating wing inboard panels and brackets on missile motor casing to have better control over weld fusion depth thus reducing welding penetration.
[0048] Some embodiments of the subject matter enable to provide the system and method for fabricating wing inboard panels and brackets on missile motor casing to eliminate inner surface oxidation by creating inert atmosphere.
[0049] Some embodiments of the subject matter enable to provide the system and method for fabricating wing inboard panels and brackets on missile motor casing to optimize production cycle time.
[0050] Some embodiments of the subject matter enable to the system and method for fabricating wing inboard panels and brackets on missile motor casing to achieve repeatability.
[0051] Some embodiments of the subject matter enable to provide the system and method for fabricating wing inboard panels and brackets on missile motor casing which is compact, cost effective and easy to implement.
[0052] Following is a list of elements and reference numerals used to explain various embodiments of the present subject matter.
Reference Numeral Element Description
100 system
102 Head Stock
104 Moving Column
106 Copper Backup apparatus
108 Tail Stock
110 Missile Motor Casing Assembly
116 Motor Casing
118 Wing Inboard Panel
120 CNC Machine

Equivalents
[0053] With respect to the use of substantially any plural and/or singular terms herein, those having skill in the art can translate from the plural to the singular and/or from the singular to the plural as is appropriate to the context and/or application. The various singular/plural permutations may be expressly set forth herein for sake of clarity.
[0054] It will be understood by those within the art that, in general, terms used herein, and especially in the appended claims (e.g., bodies of the appended claims) are generally intended as "open" terms (e.g., the term "including" should be interpreted as "including but not limited to," the term "having" should be interpreted as "having at least," the term "includes" should be interpreted as "includes but is not limited to," etc.). It will be further understood by those within the art that if a specific number of an introduced claim recitation is intended, such an intent will be explicitly recited in the claim, and in the absence of such recitation no such intent is present. For example, as an aid to understanding, the following appended claims may contain usage of the introductory phrases "at least one" and "one or more" to introduce claim recitations. However, the use of such phrases should not be construed to imply that the introduction of a claim recitation by the indefinite articles "a" or "an" limits any particular claim containing such introduced claim recitation to inventions containing only one such recitation, even when the same claim includes the introductory phrases "one or more" or "at least one" and indefinite articles such as "a" or "an" (e.g., "a" and/or "an" should typically be interpreted to mean "at least one" or "one or more"); the same holds true for the use of definite articles used to introduce claim recitations. In addition, even if a specific number of an introduced claim recitation is explicitly recited, those skilled in the art will recognize that such recitation should typically be interpreted to mean at least the recited number (e.g., the bare recitation of "two recitations," without other modifiers, typically means at least two recitations, or two or more recitations). Furthermore, in those instances where a convention analogous to "at least one of A, B, and C, etc." is used, in general such a construction is intended in the sense one having skill in the art would understand the convention (e.g., "a system having at least one of A, B, and C" would include but not be limited to systems that have A alone, B alone, C alone, A and B together, A and C together, B and C together, and/or A, B, and C together, etc.). In those instances, where a convention analogous to "at least one of A, B, or C, etc." is used, in general such a construction is intended in the sense one having skill in the art would understand the convention (e.g., "a system having at least one of A, B, or C" would include but not be limited to systems that have A alone, B alone, C alone, A and B together, A and C together, B and C together, and/or A, B, and C together, etc.). It will be further understood by those within the art that virtually any disjunctive word and/or phrase presenting two or more alternative terms, whether in the description, claims, or drawings, should be understood to contemplate the possibilities of including one of the terms, either of the terms, or both terms. For example, the phrase "A or B" will be understood to include the possibilities of "A" or "B" or "A and B."
[0055] Although implementations for a system and method for fabricating wing inboard panels and brackets on missile motor casing have been described in language specific to structural features and/or methods, it is to be understood that the appended claims are not necessarily limited to the specific features described. Rather, the specific features are disclosed as examples of implementation for the system and method for fabricating wing inboard panels and brackets on missile motor casing.