PROJECTOR FOR IDENTIFYING STRUCTURAL ITEMS BEHIND A FUSELAGE OF AN AIRCRAFT AND A RELATED METHOD

Abstract

A projector to project a pattern on a surface of an aircraft. The projector includes software configured to read a pattern, and a projector configured to project the read pattern onto the surface of the aircraft. The pattern is a map of structural images corresponding to the structural components mounted behind the skin of the aircraft, such as a fuselage, and frame references corresponding to predetermined visible points on the skin of the aircraft. The frame references are aligned with the predetermined visible points of the fuselage to match the pattern with the aircraft and the structural items are identified based on the structural references.

Claims

1. A projector assembly configured to project images on a fuselage of an aircraft, the projector comprising: a computer system configured access an electronically stored pattern of structures adjacent or near an inside surface of a skin of the fuselage and configured to select a selected pattern which is a portion of the stored pattern; a projector controlled by the computer system and configured to project the selected pattern as onto the fuselage; wherein the selected pattern includes: structural references representative of structural components adjacent or near an inside surface of the skin of the fuselage; and frame references that correspond to predetermined visible points on the skin of the fuselage; wherein the frame references are aligned with the predetermined visible points of the fuselage to align the selected pattern with the skin of the fuselage, and wherein, while the frame references of the selected portion are aligned with the predetermined visible points of the fuselage, the structural references in the selected patter are aligned with corresponding ones of the structural components of the fuselage.

2. The projector assembly of claim 1, further comprising optical and/or digital devices to zoom in/out the read pattern to scale the projected pattern to a desired size.

3. The projector assembly of claim 2, wherein the selected pattern further comprises coordinate axes suited to measure a scaling of the projected pattern.

4. The projector assembly of claim 1, further comprising a support device configured to support the projector and align the projector to face the predetermined visible points of the fuselage of the aircraft.

5. The projector assembly of claim 1, wherein the computer system includes an interface configured to communicate with a remote electronic storage device storing the stored pattern.

6. The projector assembly of claim 1, wherein the projector includes a high contrast projector.

7. The project assembly of claim 1, wherein the structural items of the aircraft comprise frames, stringers, joint means, longerons, fuselage mechanical supports and spars located behind the fuselage of the aircraft.

8. The project assembly of claim 1, wherein the selected pattern is based on clad thickness and stepping procedures of a composite skin of the fuselage of the aircraft.

9. The projector assembly of claim 4, wherein the support device includes a tripod configured to locate the projector to align the frame references with the predetermined visible points of the fuselage.

10. A method to identify identifying structural components of an aircraft that are adjacent or proximate an inside skin of a fuselage of the aircraft, the method comprising: retrieving reading a first selected pattern which includes information identifying and locating the structural components and frame references that correspond to visible points on the fuselage; projecting the first selected pattern onto the skin of the fuselage; adjusting the projection of the first selected pattern to align the frame references with the corresponding visible points of the fuselage to match the first selected pattern with the aircraft; and identifying and locating the structural components in the fuselage using the aligned projection of the first selected pattern displaying the information of the structural components.

11. The method of claim 10, further comprising: projecting at least a second selected pattern with at least a second projector onto the skin of the fuselage, adjusting the projection of the second selected pattern to align the frame references with the corresponding visible points of the fuselage to match the second selected pattern with the aircraft; and overlapping the second selected pattern with the first selected pattern to obtain an overlapped pattern projected onto the skin, and identifying and locating the structural components in the fuselage using the aligned projection of the overlapping first and second selected patterns displaying the information of the structural components.

Description

SUMMARY OF THE DRAWINGS

[0012] For a better understanding the above explanation and for the sole purpose of providing an example, some non-limiting drawings are included that schematically depict a practical embodiment.

[0013] FIG. 1 shows an example of a pattern according to the present disclosure.

[0014] FIG. 2 shows a section of the pattern according to the present disclosure.

[0015] FIG. 3 shows a projection of the section of the pattern according to the present disclosure.

[0016] FIG. 4 is a schematic diagram of a computing system with a projector configured to project patterns onto a fuselage.

DETAILED DESCRIPTION OF AN EMBODIMENT OF THE INVENTION

[0017] FIG. 1 shows an example of a pattern 100 according to the present disclosure. The pattern 100 can be obtained from a computing system associated with a projector (not shown in the figure) for projecting patterns according to the present disclosure. Examples of a computing system can be e.g. a laptop, a smartphone a tablet, etc. Furthermore, the projector comprises projecting means to project the read pattern onto the surface of the aircraft. The projector may be a high contrast projector. The pattern can be generated and transmitted by said computing system to the projector that comprises software to identify and retrieve the pattern from storage, and load the pattern into the projector. The software may be stored on a non-transitory device and executed by a processor or computer that retrieves the pattern from storage, reads the pattern to select the pattern 100 and configures the pattern for display by the projector. The pattern may be stored remotely from the computing system. The projector comprises wireless and non-wireless systems for receiving and loading the pattern transmitted from the computing system. The pattern 100 shows the fuselage 120 of an aircraft, numerical structural references 110 that relate to a group of structural items located behind the fuselage 120 of the aircraft and several frame references points as e.g. reference axis 115 to be aligned with predetermined visible points of the fuselage of the aircraft to accurately match the pattern with the aircraft. In some examples, the pattern 100 is based on a clad thickness and stepping of skin composites of the fuselage of the aircraft.

[0018] The group of structural items identified by the numerical structural references 110 can refer e.g. to frames, system supports, longerons, etc. In some examples, other structural elements behind the fuselage of the aircraft or even full systems of the aircraft as e.g. electric system, ventilation system, pressurization system, etc. can be spotted by the proposed projector. Furthermore, FIG. 1 shows a pattern section 130 chosen to be projected with the projector. Hence once the pattern section 130 is correctly projected onto fuselage of the aircraft, it is easy and quick to identify and locate any structure item or system behind the fuselage skin.

[0019] The equipment can be based on commercial off-the-shell (COTS) product provided by a third party in order reduce costs. The projector can include purchased software as e.g. a media player that permits the projection of any section of the pattern 100 on the surface of the aircraft. In some examples, the projector can comprise a tripod that ensures the right height for projection. The tripod also gives stability to the projector for a correct functioning of the projector and gives a proper positioning of the projector achieved by aligning the frame references with the predetermined visible points of the fuselage to match the pattern with the aircraft.

[0020] FIG. 2 shows the pattern section 130 selected to be projected by the projector (not shown in this figure). The pattern section 130 includes numerical references to structural items located behind the fuselage of the aircraft, e.g. frames, systems supports, longerons, etc.

[0021] FIG. 3 shows a projection 300 of the pattern section 130. The projection 300 is performed by the proposed projector on the outer surface of the fuselage of the aircraft in order to map out structural items behind the fuselage and which are identified by the numerical structural references included in the pattern section 130.

[0022] FIG. 4 illustrates a portable computing system 200 mounted to a tripod 202 near an aircraft 204. The computing system includes a projector 206 that projects a pattern section 130 onto a portion 208 of the skin of the fuselage. The section 130 identifies components, such as stringers and formers and stringers, adjacent or near an inside surface of the fuselage onto which the pattern is projected. The projected section 130 is retrieved, e.g., downloaded, by the computing system 200 from an electronic storage device that stores an electronic pattern of, for example, all structures adjacent or near an inside surface of the skin of a fuselage, wing or other section of an aircraft. The retrieval may be by a wired or wireless path 212, and the path may include access via the internet.

[0023] The projected section 130 is aligned with the fuselage by adjusting the projection to align with known frame reference points 115 visible on the outside of the fuselage. The projected sections 130 may include images of the frame reference points 115. The frame reference points 115 may be at or near the outer edges of the projected section or at two, three or more locations within the projected section 130.

[0024] The computer system and projector, automatically or manually, adjust the projected section to align the physical reference points on the fuselage with the projected frame reference points 115 in the projected section. The adjustment of the projected section may include enlarging or shrinking, e.g., zooming in or out, the projected section, shifting the section along the fuselage, and retrieving portions of the stored patterns of the entire fuselage to correspond to the physical reference points on the portion of the fuselage on which the projected section 130 is to be projected.

[0025] Even though reference has been made to a specific embodiment of the invention, it is obvious for a person skilled in the art that the lightning protector described herein is susceptible to numerous variations and modifications, and that all the details mentioned can be substituted for other technically equivalent ones without departing from the scope of protection defined by the attached claims.

[0026] While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms comprise or comprising do not exclude other elements or steps, the terms a or one do not exclude a plural number, and the term or means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.