CA2362712A1 - Inspection device for aircraft - Google Patents

Abstract

An aircraft visualization system (200) that is capable of visualizing relatively inaccessible portions of an aircraft includes a support (221) having a proximal end and a distal end, and a camera (230) that is mounted to the distal end of the support (221). The camera (230) is movably mounted to the distal end of the support (221) for movement, relative to the distal end of the support (221). In one embodiment the support (221) is extendable and is disposed at a distal end of an elongated support (211). The extendable support (221) can be extended in a direction other than a longitudinal axis of the elongated support (211), such that the system (200) can be inserted into a confined space and the camera (230) then extended in a direction other than the direction of insertion. The camera (230) is movable mounted to the distal end of the extendable support (221), and can be rotated and pivoted . The visualization system is capable of generating and storing digital images, and portions of the visualization system may be used with conventional optical imaging equipment to realize the many benifits of digital imagery.

Description

INSPECTION DEVICE FOR AIRCRAFT
Field of the Invention The present invention is directed to an imaging system. and more particularly, to an imaging system for visualizing relatively inaccessible regions of an aircraft or other inaccessible areas.
Description of the Related Art Aircraft are routinely visually inspected to ensure their safe operation.
However.
o many regions of an aircraft are relatively inaccessible and direct visual inspection is difficult if not impossible. 'these regions include. but are not limited to. the aircraft's engines. the aircraft~s structural airframe. the aircraft's rudder. stabilizers. flaps, and other steering controls, the aircraft's fuel cells, the aircraft's instrumentation panels.
cockpit wiring harnesses, etc. For example. because most aircraft en~~ines are confined within an engine 15 housing with only the inlet and exhaust portions of the engine being externally visible.
specialized visual inspection equipment is necessary to view the interior regions of the aircraft's engines. For this purpose. portions of the aircraft engine housing and portions of the aircraft engine typically include a number of small openings by which specialized viewing instruments can be inserted to inspect the interior of the aircraft's engine.
3o To date. most of the specialized visual inspection equipment that is used to inspect aircraft has been taken directly from the medical industry with little or no modification. In particular. where laparoscopes, colonoscopes. arthroscopes. and other forms of endoscopes were originally designed for use in performing minimally invasive surgical and diagnostic procedures. these instruments are now being used in a number of other applications.
35 including the visual inspection of aircraft. V~'hen used in non-medical applications. these visual inspection instruments are commonly called borescopes.
Borescopes used in the visual inspection of aircraft generally fit into two categories:
rigid borescopes and flexible borescopes. Rigid borescopes generally include a rigid.
typically cylindrical. hollow tube or borescope body with an objective lens disposed at a 3o distal portion of the body and an eyepiece disposed at a proximal eIld of~
the body. The objective lens may be disposed in line with a longitudinal axis of the body for viewing _7_ objects that are straight ahead. or disposed at an angle to the longitudinal axis of the body for viewing objects that are disposed at a fixed angle obliquely ahead.
Flexible borescopes generally include a flexible. typically cylindrical, hollow tube or borescope body having a distal end and a proximal end, with an objective lens disposed at the distal end and a camera or eyepiece disposed at the proximal end. Enclosed within the body is one or a number of optical fibers that extend from the distal end to the proximal end of the body and transmit images from the objective lens to the camera or eyepiece.
Other optical fibers may be enclosed within the body to illuminate the object being viewed.
Some flexible borescopes permit an analog image of an object that is transmitted to the camera or the t o eyepiece to be displayed on an external monitor.
Current ~~eneration flexible borescopes are either straight, two-way articulating, or four-way articulating. Straight flexible borescopes arc simply inserted into an opening and pushed distally toward the intended object, with the contours of the opening in which the borescope body is inserted forcing the body of the borescope to bend in the appropriate t5 manner. Two-way and four way flexible borescopes typically include a mechanism (frequently a wire cable, a number of wire cables. or other mechanical control) that permits the distal end (termed the "head") of the body to be moved in two or four, typically orthogonal, directions relative to the adjacent portion of the body. Movement is controlled remotely from the distal end of the body via knobs, or pulleys. Flexible borescopes make it 20 possible to see around corners inside of the ori~~inal insertion point and can snake through a set of pipes or travel down one's digestive tract (a frequent medical application).
A problem with both rigid and flexible borescopes is that their design, which was originally intended for medical purposes. is ill-suited for use in many non-medical applications, such as the visual inspection of aircraft. In particular. rigid borescopes 35 generally require that the operator be positioned so that his/her eye is aligned with the eyepiece at the end of the borescope. In the area of aircraft inspection. this positioning of the operator can be quite difficult to achieve. Furthermore, even with an angled borescope that is capable of viewing objects that are not aligned along the longitudinal axis of the body of the borescope, when a different direction of view is desired, the repositioning of the distal end of 30 the scope results in a repositioning of the proximal end of the scope. It should be appreciated that within the tight confines of an aircraft engine. an instrument panel.
etc.. there may not be sufficient room to reposition the distal end of the scope. In addition. most rigid borescopes require the use an external light source to illuminate the object being viewed.
As noted above. some flexible borescopes permit an image of an object to be displayed on an external monitor, and thus do not require that an operator be physically adjacent the distal end of the scope. . Further. because some flexible borescopes permit their distal end to be remotely moved relative to an adjacent portion of the scope.
certain movements of the distal end may be made without repositioning the proximal end.
Nonetheless, for movement in a direction other than those predefined directions, the proximal end of the scope must be moved to reposition the distal end. Moreover, even where the t o direction of movement is such that it may be remotely performed without repositioning the proximal end of the scope. such movement may not be possible due to the shape and/or dimensions of what may be a confined space in which the distal end is placed.
Furthermore, it should be appreciated that the very flexibility of flexible borescopes limits their usefulness in aircraft inspection as the body of the scope must frequently traverse large distances to t 5 reach the intended target. Flexible medical laparoscopes are typically incapable of spanning large distances without sagging, absent some additional support structure.
Hence when such flexible borescopes are used for aircraft inspection, they are frequently inserted into a pipe for support.
Because the use of technology developed for the medical industry is ill-suited for the ?o inspection of aircraft, its use, when possible, often results in the false detection of problems, when no problem actually exists. To ensure the safety of passengers and the public, whenever even a suspected problem is detected. the aircraft is typically removed from service and then dismantled to determine whether a problem actually exists. In the event that there is no actual problem with the aircraft. then a great deal of time and money has been wasted. For 25 example. with respect to the visual inspection of aircraft engines, it is estimated that five out of every eight aircraft engines are pulled out of service unnecessarily. It should further be appreciated that each time an aircraft is removed from serv-ice and a portion of the aircraft is dismantled to determine if an actual problem exits. there is a possibility for the re-assembly to be performed improperly, thereby creating a problem where none existed before.
30 Alternatively, where the use of a conventional medical technology results in not detecting a problem that actually does exist, the effects of such an error can be catastrophic.

Summar<~ of the Invention According to an aspect of the present invention, an aircraft visualization system is provided that is capable of visualizin~~ relatively inaccessible regions of an aircraft, such as the aircraft's en~Tine. the aircraft's rudder. stabilizers, Claps. and other steerin~~ controls, the aircraft's fuel cells, the aircraft's cockpit. etc. It should be appreciated that although embodiments of the present invention are described with reference to an airplane, the present invention is not so limited, as embodiments of the present invention may be used to inspect helicopters. gliders. and other fixed-wing and non-fixed wing aircraft.
Moreover, use of the present invention is not limited to the aviation or transportation fields. as embodiments of the present invention may be used to inspect any object that can be difficult to access and view directly. Thus. exemplary uses for embodiments of the present invention include inspecting underground stora~~e tanks. inspecting turbines used in electrical generators, military tanks or transports or other land, water, or airborne vehicles, etc.
According to one embodiment of the present invention, aircraft inspection apparatus 15 is provided. The aircraft inspection apparatus includes a support having a proximal end and a distal end and a camera that is mounted to the distal end of the support. The camera is movably mounted to the distal end of the support for movement relative to the distal end of the support.
Accordiny~ to another embodiment of the present invention. a method of inspecting an 2o aircraft is provided for a camera that is mounted at a first position to a distal end of an elongated support. The method includes acts of inserting the camera into a portion of the aircraft and moving the camera to a second position that is spaced apart from the first position without changing a position of a proximal end of the elongated support.
According to further embodiment of the present invention, another method of 25 inspecting an aircraft is provided. The method includes acts of inserting a camera that is mounted to a distal end of an elongated support into a first portion of the aircraft, the camera being mounted to the distal end of the elongated support at a first position, and telescoping the camera to a second position that is spaced apart from the first position.
According to another embodiment of the present invention. a method of inspecting an 3o aircraft is provided that includes acts of inserting a camera that is mounted to a distal end of a support into a portion of the aircraft. the distal end of the support being in a first position inside the portion of the aircraft. and remotely telescoping the support to a second position inside the portion of the aircraft.
According to vet another embodiment of the present invention, a method of inspecting ar.
aircraft is provided that includes acts of inserting a camera that is mounted to a distal end of a support into a portion of the aircraft and illuminating the portion of the aircraft with a light source that is disposed adjacent to the camera.
According to another embodiment of the present invention a further method of inspecting an aircraft is provided. The method includes acts of inserting a camera that is mounted to a distal end of a support into a portion of the aircraft, generating a digital image of 1 o the portion of the aircraft, transmitting the digital image of the portion of the aircraft to a storage device, and storing the digital image on the storage device.
According to another embodiment of the present invention, a method of inspecting an aircraft is provided that includes acts of inserting a camera that is mounted to a distal end of a support into a portion of the aircraft and telescoping the camera in a direction other than along a longitudinal axis of the support.
According to a further embodiment of the present invention, a method of inspecting an aircraft with a conventional borescope is provided. The method includes acts of inserting the borescope into a portion of the aircrafr, the borescope having an eyepiece, coupling a digital camera to the eyepiece of the borescope, and generating a digital image of the portion of the aircraft.
Brief Description of the Drawings Illustrative, non-limiting embodiments of the present invention are described by way of example with reference to the accompanying drawings, in which:
Figure lA is a frontal view of a conventional aircraft jet engine;
Figure 1B is a schematic cross-sectional view of a conventional aircraft jet engine;
Figure 1 C is a fragmentan~ enlarged perspective view of a portion of the jet engine of Figure 1 B;
Figure 2A is a perspective view of an aircraft visualization system according to one 3o embodiment of the present invention;
Figure 2B is a perspective view of an aircrafr visualization system according to another embodiment of the present invention;
RECTIFIED SHEET (RULE 91) ISA/EP

Figtwe 3A is a perspective view of an aircrafr visualization system according to another embodiment of the present invention:
Figure 3B is a perspective view of an aircraft visualization system according to another embodiment of tire present invention;
Figure 4 is an enlarged fragmentan~ perspective view of a telescoping support and camera assembly that may be used v~zth any of the embodiments of Figures 2A.
?B. ~A. and 3H;
Figure ~ is a front elevationai view of an aircraft visualization system according to another embodiment of the present invention;
Figure 6A is a perspective view of outwardly visible aspects of a mufti-positional ca.-nera to module that may be used with the visualization system of Figure 5;
Figure 6B is an alternative perspective view of t.~:e mufti-oositional camera module of Figure 6A;
Figure 7A is a cross-sectional view of some of the internal aspects of a mufti-positional camera module of Fisures 6A and 6B;
15 Figure 7B is an alternative cross-sectional view of the internal aspect of the multi-positional camera module of Figure 7A;
Figure 8 is a cross-sectional view of internal aspects of the aircraft visualization system of Figure 5;
Figurtr 9 is a perspective view of the aircrafr visualization system of Figure ~ in a fully 2o extended position;
Figure 10 is a functional block diagram of an optical imaging system according to one aspect of the present invention;
Figure 1 I is an exploded front view of an imaging device in accordance with one embodiment of the prrscnt invention;
25 Figure 12 is a partially cutaway side elevationaI view of the imaging device of Figure 11;
Figure 13 is a cutaway top view taken through plane I = - I 3 in Figure 1 I , of a sheath cap in the imaging device of Figure I 1;
Figure 14 is as enlarged cutaway side view of the upper housing and the lo~vcr portion of the imaging device of Figure I 1;
30 Figure 15 is a cutaway top view of the upper housing of the imaging device of Figure 11 taken through plane IS-IS in Figure 14;
RECTIFIED SHEET (RULE 91) ISA/EP

Figure I 6 is a cutaway top view of the lou-er portion of the imaging device of Figure 11 taken through plane 16-16 in Figure 14;
Figure 17 is a functional block diagram of a system for controlling the imaging device of Figure 1 l and for displaying the images transmitted by the imaging device;
Figure 18 is a functional block diagram of an alternate control and display system for the imaging device of Figure 11;
Figure 19 is an exploded cutaway side view of an alternate embodiment of a surgical/diagnostic imaging device in accordance with the present invention;
Figure 20 is a front view of the camera housing of the image deuce of Figure 19: and Figure 21 is a cutaway side view of the camera housing taken through plane 21-21 in Figure 20.
Detailed Description Embodiments of the present invention will be understood more completely through the following detailed description which should be zeal in conjunction with the attached drawings in which similar reference numbers indicate similar structures.
While the embodiments of the present invention are described below in connection with use in aircraft inspection, it should be appreciated that the described systems can be used in numerous other applications for viewing in confined or otherwise inaccessible areas. Thus, the embodiments of the present invention described are not limited to use in an aircraft visualization environment.
Figure lA is a frontal view of a conventional aircrafr let engine 100 looking toward the turbine blades 140 of the jet engine 100. As shown in Figure lA, the engine 100 is disposed within an engine housing I 10. The engine I00 can be accessed via a small opening I20 in the engine housing 110. Interior regions of the engine 100 can be examined via a small opening I30 in the engine 100 that is aligned with the opening 120 in the engine housing 110.
Figure IB is a cross-sectional view of the aircraft jet engine 100 shown in Figure lA.
As shown in Figure IB, the engine 100 includes a plurality of small openings or viewing holes I30 through which various interior regions and parts of the engine 100 may be inspected. In Figure 1 B, these openings 130 arc labeled with reference indicators A-H.
3o Some of these openings (e.g., openings A and F) can only be accessed using a flexible botrscope while others can be accessed using a rigid borescope (e.g., openings B - E, G, and H). Furthermore. many of the interior portions of the engine 100 can only be viewed from a RECTIFIED SHEET (RULE 91) ISA/EP

direction that is perpendicular to the direction in which the borescope is inserted in the engine 100. It should be appreciated that depending on the size of the aircraft engine 100 (e.g., an engine of a Boeing 757 or an engine of a Lean jet), the distance between the opening 130 in the engine through which the borescope is inserted and the intended object to be view can be quite large, on the order of several feet.
Figure I C is a fragmentan~ enlarged perspective view of various internal components of the aircraft jet engine afFigure IB showing some of the internal components that are conventionally subject to periodic visual inspection.
Figure 2A illustrates an aircraft visualization system according to one embodiment of the 1 o present invention. The aircrafr visualization system 200 includes an imaging component attached to a telescoping support 221.
In one embodiment, Lhe imaging component is a charged coupled device (CCD), but it should be appreciated that the invention is not limited in this respect as other imaging devices caa be employed. In the embodiment shown, the aircrafr visualization system 200 also includes 15 a light 235 attached to the telescoping support 221, to illuminate the area viewed by the imaging device. In one embodiment of the invention, the light is a light source (e.g., a light bulb) that generates light. However, it should be appreciated that the present invention is not limited in this respect and the light can alternatively be a fiber optic bundle that carries Light, generated from an external light source, to the viewing area. However, the use of a light source mounted 20 to the telescoping support 221 is advantageous, in that it can be cheaper than using a fber optic system, and also enables the system to be used without a light source for a Tiber optic bundle which can be rather large and inconvenient to transport.
Telescoping support 221 is attached to a distal end of an elongated support 211, with the proximal end of the elongated support 211 being attached to a handle 240. In the embodiment 25 shown in Figure 2A the telescoping support 221 is disposed at an angle that is perpendicular to the elongated support 211. This permits the hand held portion of the aircrafr visualization system 200 to be inserted into a small opening and then extended in a direction perpendicular to the direction of insertion. However, it should be appreciated that the present invention is not limited to a telescoping support 221 that is disposed perpendicular to a longitudinal axis of the 30 elongated support 211, as other orientations may be used.
The handle 240 includes a number of controls 260 that control the operation of the CCD
camera 230, the light source 235, and the telescoping support 221. Images obsen~ed by RECTIFIED SHEET (RULE 91) ISA/EP

the CCD camera 230 are relayed to a monitor and/or a storage device (not shown] via cable 250. In one embodiment. the telescopin;~ support'_21 is capable of retracting into a position that is flush with the outer surface of the elongated support 211 to permit easy insertion through the openings 120, 130 in the engine housing 1 10 and the engine I 00 (Figure 1 ). In another embodiment. the telescoping support 221 is capable of retractin~~ into a position that extends beyond the outer surface of the elongated support 2 I I . but is still capable of insertion through openings having a small diameter. for example four millimeters.
In operation. the distal end of the elongated support 21 I is inserted through the opening 120 in the engine housing I 10 and the opening 130 in the engine 100.
Once inserted o through these openings. controls 260 are used to extend the telescoping support 221, and thus, the CCD camera 230 and light source 235 to the desired position. In addition to providing the ability to extend and retract the telescoping support 221, controls 260 include individual controls for taking a still picture. for zooming in or out on a selected target, for rotating the CCD camera 230 and the light source 235 about the longitudinal axis of the telescoping support 221, and for adjusting the elevation of the CCD camera 230 and light source 235. Advantageously, the field of view of the camera 230 can be changed without changing the position of the distal end of the handle 240, and without requiring any additional space in which to perform such rotation. In one embodiment, the CCD camera 230 can be rotated from zero to 360 °
3o Controls 260 may include a rotary dial 262 that can be manipulated by an operator's thumb to extend or retract the telescoping support 221. a rocker switch or joystick 264 that can be used for rotating the CCD camera 230 and the light source 235 left or right about a longitudinal axis of the telescoping support 221 and for adjusting the elevation of the CCD
camera 230 and the light source 235 upward or downward. The controls 260 may also '?5 include one or a number of other buttons 266 that may be used for taking a still picture at a particular moment in time or for taking a series of pictures over a period of time (i.e., a moving picture). for zooming in or out on a selected target, or for turning on and off the light source 23~. It should be appreciated that this explanation of potential use of controls 260 is merely provided for illustration. as numerous additional or alternative controls can be 3o provided, and mechanisms other than a rotary dial or joy stick can be employed for implementing the controls 260.

In the embodiment shown in Figure 2A, the visualization system 200 also includes a local display 270 mounted on the handle 240 that is used to provide the operator of the system with a continuous image of what is being viewed by the CCD camera. In this manner, an operator can remotely maneuver the CCD camera into a desired position and then take a still picture of the area of interest when desired. In one embodiment. one of the controls 260 may also be used to enter a menu-based control program that can be displayed on the local display 270. After entering the menu-based control program, others of the controls 260 can be used for navigating the menus shown on the local display 270, such as for adjusting picture quality (e.g., white balance, contrast, etc.) of the CCD camera 230.
etc.
As noted above. the visualization system 200 can include a monitor and/or storage device to view and store images observed by the CCD camera 230. For example images may be stored on any type of storage medium. including a hard drive, a CD, a floppy disc. a RAM
card, etc. The visualization system 200 can also include a keyboard or other input device by which the operator can provide detailed information relating to the object being viewed. For l5 example, the operator can identify the type of aircraft engine being inspected, the make, model number and registration number of the aircraft, the name of the operator, the date the inspection was performed, as well as other information that would be useful during such an inspection. The visualization system may also include another input device, such as a pointer or mouse, for highlighting a specific region of interest. For example. a particular region of 2o the engine could be highlighted. or placed within a border to call attention to a particular detail. This feature may be used, for example, to place a watch on a particular region of the engine that may be prone to excessive wear. By comparing photographs of this particular region over time, it can be possible to detect problems before they result in actual failure.
Moreover. it should be appreciated that photographs of a particular region of interest may be 25 compared to photographs of the same region in failed engines or in known good engines by an expert system to detect signs of incipient failure. In addition, because the embodiment of Fig. 2A utilizes digital technolo~~y, photographs taken by the visualization system 200 may be easily sent to a remote location using conventional communication networks (e.~~.. the Internet). Thus, rather than being dependent upon local experts to review inspection data, or 3o having other experts transported to the inspection site. photographs may be sent electronically to those most knowledgeable with the system of interest. Although the use of digital technology provides a number of advantages, it should be appreciated that the invention is not limited to the use of digital technology.
Figure 2B illustrates an aircraft visualization system according to another embodiment of the present invention. The aircraft visualization system 201 is similar to the aircraft visualization system 200 of Figure 2A in most respects, with the same reference designators identifying similar structures. However. in the embodiment of Figure 2B, the visualization system 201 does not include a local display 270 that is mounted adjacent the handle 240.
This reduces the size and weight of the hand-held portion of the visualization system 201, and permits its use within even more confined regions of the aircraft. To permit the operator to t 0 position the CCD camera 230, the visualization system 201 includes a battery operated computer control module 271 that includes a CPU, a monitor, and a storage device for displaying pictures of objects viewed by the CCD camera 230 and for storing those pictures on the storage device. The control module 271 is coupled to the hand held portion of the visualization system via cable 250. Advantageously, the storage device may include a l5 removable RAM module (e.g., a PCMCIA RAM card) to reduce the size and weight of the control module 271. It should be appreciated that solid state types of storage devices such as RAM modules are less prone to damage from environmental conditions. changes in orientation, and impacts with other objects (such as from dropping the storage device) than many other forms of storage media. After use of the visualization system 201, the storage 2o device can be removed from the control module 271 and pictures stored thereon may be transferred to another computer system. In one embodiment, the computer control module 271 is configured to attach to the belt of an operator to permit hands-free operation. It should be appreciated that the control module 271 need not be attached to the belt of an operator, as the control module 271 may be positioned wherever it is most convenient.
25 Figure 3A illustrates an aircraft visualization system according to another embodiment of the present invention. The aircraft visualization system 300 is similar to those described with respect to Figures 2A and 2B above. However, in contrast to the visualization systems 200 and 201 of Figures 2A and 2B. telescopin~~ support 320 is attached to the distal end of elongated support 310 by a hinge 325. Hinge 32~ is used to allow the 30 telescoping support 320 to extend significantly farther than the telescoping support 221 of Figures 2A and 2B. Hinge 325 allows telescoping support 320 to move along arrow 345 from a closed position, wherein the telescoping support 320 is recessed in the elongated support 310 within groove 315, to the open position shown in Figure 3A. Hy using hinge 325, the telescoping support 320 can have a fixed portion 365, that, when moved to the open position, permits the CCD camera 330 and Iight source X35 to be placed in an already extended position.
Where further extension is desired. telescoping portion 35~ can then be extended. In this manner, the CCD camera 330 and light source 335 can be extended great distances nom the elongated support 310.
As shown in Figure 3 A, visualization system 300 also includes a handle 340 that is attached to the proximal end of the elongated support 310. The handle 340 includes a number of controls 360 for controlling the operation of the CCD camera 330, the Iight sourt~e l0 335, and the extension and retraction of the telescoping portion 355 of the telescoping support 320. Controls can also be provided, for example, to move fixed portion 365 from its closed position recessed within groove 315 to the open position. to take a series of pictures over a period of brae or a still picture at a particular moment in time, for zooming in or out on a selected target, for rotating the CCD camera 330 and the Iight sotuce 335 about the t5 longitudinal axis of the telescoping support 320, and for adjusting the elevation of the CCD
camera 330 and light source 335. As in the embodiment described with respect io Figure 2A, images observed by the CCD camera 330 of visualization system 300 can be relayed to a monitor andlor a storage device (not shown) via cable 350.
Figure 3B illustrates an aircraft visualization system 301 according to another 20 embodiment of the present invention. The aircraft visualization system 301 is similar to that described in Figure 2B, in that the visualization system 301 dispenses with a local display on the hand held portion of the visualization system 301. As in the embodiment described with respect to Figure 2B, the visualization system 301 includes a computer control module 371 that is coupled via cable 350 to the hand-held portion of the system and can be used for 25 storing and viewing pictures of an object. The visualization system 301 is also similar to the embodiment described with respect to Figure 3A, in that the telescoping support 320 is attached to the distal end of elongated support 3 I 0 by a hinge 325. Hinge 325 again allows telescoping support 320 to move along arrow 345 from a closed position, wherein the telescoping support 320 is recessed in the elongated support 310 within groove 315, to the 30 open position shown. However, in contrast to the embodiment of Figure 3A, telescoping support 320 does not have a fixed portion 365. This permits the CCD camera 330 to RECTIFIED SHEET (RULE 91) ISA/EP

incrementally move from a position adjacent to the elongated support 310 to its maximum length.
In a manner sinular to that of Figures 2A, 2B, and 3A, the visualization system 301 may include a charge coupled device camera 330 and light source .35 that are attached to the telescoping support 320, and controls 360 to move the telescoping support 320 from its closed position recessed within groove 315 to the open position. to take a series of pictures over a period of time or a still picture at a particular moment in time. for zooming in or out on a selected target, for rotating the CCD camera 330 and the light source 335 about the longitudinal axis of the telescoping support 320, and for adjusting the elevation of the CCD camera 330 and 1 o light source 335.
Figure 4 is an enlarged fragmentary perspective view of a telescoping support and camera assembly that may be used with any of the embodiments of Figures 2 A, 2B, 3A. and 3H.
As shown in Figure 4, the camera assembly 400 includes a CCD camera 430 including a CCD
imaging device 432 and a lens 431. Advantageously the CCD imaging device 432 and the lens 15 431 may be formed as a unitary structure such that no focusing of the lens 431 zelative to the CCD imaging device 432 is necessary. In one embodiment, the lens 431 may include a constant focus lens assembly such as that described in co-pending U.S. Patent Application Serial Number 09/I26,368 (hereafter the '368 application), filed July 30, 1998, and entitled IMAGING
DEVICE, in which the applicant is a named inventor. The '368 application describes a Lens Zo assembly that includes a distal Lens, a doublet Lens. and a proximal lens that are bonded together and permit high resolution images to be taken of any object that is more than approximately one inch away from the kns assembly without requiring the use of focusing or lens positioning equipment. While the lens described in the '368 patent is particularly advantageous in view of its constant focus properties, it should be appreciated that the present invention is not limited to 25 using this lens assembly, as numerous other lenses can alternatively be employed.
The camera assembly 400 may also include one or a plurality of light sources 435 that are mounted adjacent to the CCD camera 430. In the embodiment shown in Figure 4, two Light sources 435 are disposed at opposing sides of the CCD camera 430, althouga more or fewer light sources 435 may alternatively be used. In one embodiment, the light sources 435 30 include miniature incandescent bulbs that are capable of providing illumination that is far brighter and more diffuse than a conventional fiber optic light source. It should also be RECTIFIED SHEET (RULE 91) ISA/EP

appreciated that should one or more of the incandescent bulbs be damaged or burn out. they may be replaced at a much lower cost than a conventional fiber optic light source. Of course, as discussed above, the present invention is not limited to employing light sources adjacent the camera assembly 400, as a fiber optic light source can alternatively be employed.
The camera assembly 400 is disposed within a gimbled camera housing 450 that is mounted to a top ring 421 of the telescoping support 420 for rotation about a shaft 422. The top ring 421 of the telescoping support 420 is capable of rotating anywhere between zero and 360° relative to the longitudinal axis of the telescoping support 420.
The gimbled camera housing 450 is capable of rotating in elevation about the shaft 422 from approximately 20°
t o below horizontal to over 90° above horizontal. It should be appreciated that because the gimbled camera housing 450 is entirely recessed within the top ring 421 of the telescoping support 420, the field of view of the camera assembly 400 can be elevated, depressed and/or rotated without requiring any additional space other than that required to receive the top-most ring of the extendable support. This is in contrast to rigid and flexible borescopes in which 15 movement of the head of the borescope from one position to another typically requires additional space. Although the particular gimble mount shown in Figure 4 is advantageous, it should be appreciated that the present invention is not limited in this respect, as the camera assembly 400 could be mounted to the telescoping support 420 in numerous other ways.
Figures 5-9 illustrate an aircraft visualization system according to yet another 20 embodiment of the present invention. In contrast to embodiments depicted in Figures 2-4, the visualization system illustrated in Figures ~-9 is configured to extend and retract a camera assembly significant distances along a longitudinal axis of a telescoping support. As in the embodiments described with respect to Figures 2-4, the camera assembly is capable of changing its position both rotationally and elevationally.
25 The visualization system 500 includes a mufti-positional camera module ~ 10 and a telescoping support 520. Advantageously, the mufti-positional camera module 510 can be easily connected and separated from the telescoping support 520. This permits the multi-positional camera module 510 to be used with different telescoping supports 520 of varying lengths, depending upon the requirements of the task at hand. For example. to inspect a 30 horizontal or vertical stabilizer in the tail of an aircraft, an extended length of up to eight feet may be required. For other tasks, such as inspecting the wiring harness of the instrument console in the cockpit of the aircraft. a length of only two feet may be required. Accordingly, a number of different telescoping supports 520 may be provided, each having a different length when fully extended. In one embodiment of the present invention, four different sizes of telescoping supports are provided, one with an extendable length of approximately 2 feet, another with an extended length of approximately 4 feet, another with an extended length of 5 approximately 6 feet, and another with an extended length of approximately 8 feet.
It should be appreciated that because the mufti-positional camera module 510 may be easily removed from one telescoping support 520 and attached to another, a single multi-positional camera module 510 can be used to perform a variety of tasks.
Furthermore, should either a telescoping support 520 or the mufti-positional camera module S 10 be dropped or 10 otherwise damaged during use, a new mufti-positional camera module 510 or support 520 may be provided. It should be appreciated that in a conventional borescope, should any portion of the borescope be damaged during use, it is typically required that the entire instrument be replaced as a whole. .
Figures 6A and 6B show different perspective views of the outwardly visible aspects of 15 the mufti-positional camera module 510, whereas Figures 7A and 7B show different cross-sectional views of some of the internal aspects of the mufti-positional camera module 510. In a manner similar to that of embodiments of Figures 2-4, the mufti-positional camera module 510 includes a camera assembly 600 having a CCD camera 630. The CCD camera, in tum, includes a CCD imaging device 632 and a lens 631. Again, in one embodiment the CCD
imaging device 632 and the lens 631 optionally may be formed as a unitary structure in a manner similar to that described in the '368 application, such that no focusing of the lens 631 relative to the CCD
imaging device 632 is necessary.
The camera assembly 600 also includes a plurality of light sources 635 that are mounted adjacent to the CCD camera 630. In the embodiment shown, two light sources 635 are disposed at opposing sides of the CCD camera 630, although more or fewer light sources 635 may alternatively be used. As in the embodiments of Figures 2-4, the Iight sources 635 may include miniature incandescent bulbs, although other sources of light can alternatively be employed.
Camera assembly 600 is disposed within a gimbled camera housing 650 that is mounted in a nose 640 of an upper portion 680 of the mufti-positional camera module 510. It should be appreciated that the illustrated placement of the camera assembly 600 within the nose 640 protects the camera assembly 600 from contact with other objects and from RECTIFIED SHEET (RULE 91) ISA/EP

potential damage during insertion of the mufti-positionai camera module 510 or extension thereof. The gimbled camera housing 650 is mounted for rotation about a shaft 6'?'' and is capable of rotating in elevation about the shaft 622 from approximately 60° below hor'.zontal to over 90 ° above horizontal. The upper portion 680 of tile mufti-positional camera module 510 is capable of rotating anywhere between zero and 360° relative to a louver portion 690 of the mufti-positional camera module 510. It should be appreciated that because the gimbled camera housing 650 is entirely recessed within the nose 640 of upper portion 680, the i:eld of view of the camera assembly 600 can be elevated, depressed and/or rotated without rea~.iiring any additional space. It should be appreciated that the ranges of motion discussed above arc 1o provided merely for illustrative purposes. as numerous other arrangements are possible.
Image signals tl~..nsmitted from tho camera assemdly 600 are conveyed to otaer portions of the visualization system 500 via a flexible cable or flex circuit 695. The flex circuit 69~ also provides power to the Light sources 635.
The lower portion 690 of the mufti-positional camera module 510 includes a ring 685 that is threaded on the inside and knurled on the outside and is used for securely mounting the mufti-positional camera module onto the telescoping support 520. The telescoping support 520, in turn, includes a threaded portion (not shown) that is adapted to mate with the zing 685 and securely attach the mufti-positional camera module thereto. Signals to alter the position of the upper portion 680 of the module with respect to the lower portion 690 of the 2o module, to alter the elevation of the camera assembly 600, to control the light sources 635, and to electronically transmit image data from the camera assembly 600 to a monitor andlor storage device (not shown) are provided via a card edge connector 698. The card edge connector 698 mates with a receptacle (not shown) in the telescoping support 520 to provide these signals to a control unit, or to a monitor and/or storage system.
a Figures 7A and 7B illustrate different cross-sectional views of some of the internal aspects of the mufti-positional camera module 510. As shown in Figure 7A, a rotation motor 710 is mechanically coupled to a bearing surface 712 on the upper portion 680 of the multi-positional camera module S I 0 for rotation of the upper portion 680 relative to the lower portion 690. An elevation motor 720 is disposed above the bearing surface 712 and engages an 30 elevation shaft 715 that is coupled to the gimbled camera housing 650 for altering the elevation of the gimbled camera housing 650, and thus the camera assembly 600 about the shaft 622. A
printed cirettit board 730 provides electronic circuitry for amplifying and RECTIFIED SHEET (RULE 91) ISA/EP

processing image signals from the CCD camera 630. The printed circuit board 730 is electrically coupled to the flexible circuit 695 and the card edge connector 698. T'ne printed circuit board 730 also transmits power and control signals to the motors 710, 720, and to the light sources 63 S. Details of a mufti-positional camera module that may be used in the visualization system are described further below with respect to Figures 10-21. Although the particular implementation of the camera module of Figures 10-21 provides a number of advantages, ii should be appreciated that the present invention is not limited to this implementation, as numerous others are possible.
Figure 8 is an exposed cross-sectional view of the aircraft visualization system 500 of to Figure S. As described above, the aircraR visualization system includes a mufti-positional camera module 510 and a telescoping support 520. Referring now to the telescoping support 520, two bearings 815 and 820 are disposed on opposite sides of a flat tape 8I7 that is attached to a base 835 of each of a plurality of rings 836. A motor 810 engages bearing 815 causing bearings 815 and 820 to rotate in one of two opposing directions. When bearing 815 rotates i5 counterclockwise (and bearing 820 rotates clockwise), flat tape 8I7 is pushed upwardly in Figure 8 to extend the rings 836, and thus, mufti-positional camera module 510. Alternatively, when bearing 815 mtates clockwise (and bearing 820 rotates counterclockwise), flat tape S I7 is pulled downwardly in Figure 8 to retract the zings 836 and thus, mufti-positional camera module S 10. In a fully retracted position, excess portions of the flat tape 817 are coiled about a spindle 2o 840 in a base 830 of the telescoping support. It should be appreciated that other forms of achieving the extension of the telescoping support may alternatively be provided as the present invention is not limited to any particular implementation.
Figure 9 illustrates aircraft visualization system of Figure 5 in a fully extended position.
Controls 960 for extending and retracting the telescoping support, for rotating the camera 25 relative to the longitudinal axis of the telescoping support, and for changing the elevation of the camera assembly 600 arc provided at the base 930 of the system. Images transmitted by the CCD camera are provided to a monitor and display (not shown) via a cable 950 Figure 10 is a functional block diagram of an optical imaging system that is suitable for use with the embodiments of the present invention discussed above. As shown in Figure 30 10, the optical iazaging system 1000 includes a camera head I 070 that is coupled to a camera RECTIFIED SHEET (RULE 91) ISA/EP

body 1080. Camera head 1070 includes a lens assembly 1010 and an imaging device 1020.
Light from a target enters lens assembly 1010 and is focused on the imagin~l device 1020. In one embodiment, the imaging device is a charge coupled device (CCD). However, it should be appreciated that the imaging device 1020 can alternatively be of another type. such as a S microbolometer array (e.g., an infra-red detection array) that is capable of perceiving objects at very low levels of light, as the present invention is not limited to the use of a CCD as the imaging device.
Imaging device 1020 includes a plurality of pixel elements (e.g., photo diodes) that convert light energy focused by the lens assembly 1010 into a plurality of electrical signals.
io The plurality of electrical signals from the imaging device 1020 are provided to an amplifier 1030 that is coupled to the imaging device 1020 by a connection 1090.
Amplifier 1030 amplifies each of the plurality of electrical signals from the imaging device 1020 and provides the amplified electrical signals to a camera control unit (CCU) 1040 that forms an image based on the plurality of amplified electrical signals. CCU 1040 can be a 15 microprocessor-based system that may include some memory (not shown) for temporarily storing an image prior to providing the image to a display 1050 and/or a storage (recording) device 1060. Alternatively, the CCU 1040 can provide the image directly to the display 1050 or storage device 1060. As shown in Figure 10. the display 1050 can be coupled to the storage device 1060 so that a previously recorded image (or images) can be displayed on the 2o display 1050.
According to one aspect of the present invention, the imaging device I 020 is coupled to the amplifier 1030 by a flexible connection 1090, such as a flexible cable or a flexible circuit. Accordingly, the optical elements in the camera head 1070 that focus and receive light from the target (e.g., the lens assembly 1010 and the imaging device 1020) need not be 25 in-line with the amplifier I 030 or other elements of the imaging system (e.g., those elements in the camera body 1080), and can be positionable independently therefrom.
This in contrast to a conventional camera in which the lens. the viewing aperture and the recording medium (e.g., film) are optically aligned within the body of the camera. Furthermore, flexible connection 1090 also permits the lens assembly 1010 and the imaging device 1020 to be 30 located within the camera head 1070 of the imaging system 1000. with the amplifier 1030 and the CCU 1040 being disposed in a physically separate camera body 1080. The display 1050 and storage device 1060 can be disposed in the camera body 1080 of the imaging system 1000 along with amplifier 1030 and CCU 1040. or they may alternatively be disposed in a location separate therefrom.
The physical separation of the lens assembly 1010 and the imaging device 1020 from other portions of the imaging system 1000 provides a number of advantages over conventional imaging systems in which all of these devices (i.e., the lens assembly 1010, the imaging device 1020. and the amplifier 1030) are located within the same housing. For example. separation of the amplifier 1030 from the camera head permits camera head 1070 to be significantly smaller and lighter in weight than that of conventional imaging systems.
Alternatively. for a camera head of a fixed size. this separation permits the optical elements l0 (e.g., the lens and CCD) within the camera head to be larger, thereby increasing image resolution. Furthermore, flexible connection 1090 and the small scale of the camera head 1070 permit the camera head to be pivoted and/or rotated in a confined space for viewing in a number of different directions.
The optical imaging system described in Figure 10 has been employed in a design for a surgical/diagnostic imaging device for use in interabdominal, interthoracic, and other surgical and diagnostic procedures. Examples of such a surgical/diagnostic imaging device are described in U.S. Patent No. 5,762,603 (hereinafter, the '603 patent) which is entitled "Endoscope Having Elevation and Azimuth Control of Camera Assembly'' and shares a common inventor with the present application. The technology employed in implementing the surgical/diagnostic imaging devices of the '603 patent. which are described below with reference to Figures I 1-21, can also be used in the embodiments of the present invention described above.
Figures 11-13 show an imaging device 1. The device 1 comprises an upper housing 3, a camera housing ~, and left and right camera housin~ supports 7, 9. For medical applications. the device I is inserted into a sterile sheath 11. The device 1 and sheath 11 (collectively, the "camera") are then inserted through an incision into the patient's body (not shown). The camera is inserted so as to place the camera housing ~ in a position from which it can be pointed at the surgical site or the area to be diagnosed. The incision is sealed around the camera with a purse string stitch, thereby preventing leakage of the CO~
gas which is used to distend the patient's abdomen or chest during surgew or diagnosis.
The sheath 11 may be constructed of medical-grade plastic provided in a sterilized condition, and may be intended to be disposed of after use. .Alternately. the sheath 1 1 can be constructed of heat-resistant materials to allow it to be sterilized using an autoclave. then reused. It will be appreciated that the sterile sheath 1 I eliminates the need to sterilize the camera. For non-medical applications, it may be possible to eliminate the use of the sheath.
However. for numerous non-medical applications. it may still be desired to employ the sheath s as it protects the other components of the system.
The camera housing ~ contains a CCD (not shown) and a zoom lens assembly (not shown). A plurality of high intensity lights 13 are mounted within a light housing 1 ~ which extends about the outer circumference of the camera housing 5. The lights I 3 are aligned with the focal axis 17 of the CCD. and they illuminate the area at which the camera housing ~, and hence. the CCD are pointed.
When the device 1 is inserted in the sheath 1 I, the left and right camera housing supports 7. 9 engage complimentary locking keys 19. 21 within a sheath cap 23.
As a result, the camera housing ~ is locked into a position in which the CCD's focal axis 17 is aligned perpendicular to an optically-clear window 25. In addition, as will be described below in is connection with Figures 13-I5, the locking keys 19, 21 cause the sheath cap 13 to rotate about the longitudinal axis 27 of the camera when the camera housing supports 7, 9 are rotated about that axis.
The image system of the device I can be implemented using the techniques described above in connection with the imaging system 1000 of Figure 10. The camera housing 5 can 2o include only the CCD and the lens assembly. with the amplifier 1030, CCU
1040 and other components of the imaging system being disposed outside the body of the device I . A
camera cable 29 extends between the camera housing ~ and the upper housing 3.
The camera cable 29 contains conductors which carry the CCD's signals to the upper housing 3 and which supply electrical power to the CCD and lights 13. An imaging device cable 31 is 25 provided to carry control signals and supply electrical power to the device 1, and to carry the CCD's signals to the externally-located processing. display and storage devices (not shown) of the imaging system.
The length of the camera housing supports 7, 9 and the length of the sheath I
1 can be selected to match the needs of a particular application.
3o Referring now to Figures I-1-16. an elevation motor ~l drives an elevation shaft 53 by means of gears ~~. ~7. The elevation shaft ~3 extends downwardly through the hollow left camera support 7. A ring and pinion gear arrangement ~9 at the lower end of the elevation shaft 53 transfers the rotary motion of the elevation shaft 53 to the camera housing 15, thereby causing the camera housing 15 to elevate or depress. depending on the direction of rotation of the elevation motor 51. In this embodiment of the invention. the camera housing 15 can be elevated 70 ° above and depressed 90 ° below a plane perpendicular to the longitudinal axis 27 of the camera and passing through intersection of the longitudinal axis 27 and the focal axis 17 of the camera.
The elevation motor 51 is mounted on a plate 63. The plate 63 is rotatably mounted within the upper housing 3 on a bearing 65. An azimuth motor 67 is also mounted on the plate 63. The azimuth motor 67 drives an azimuth gear 69. The azimuth gear 69 engages a 1 o housing gear 71 which is attached to the inner surface of the upper housing 3. When the azimuth motor 67 rotates. the plate 63 rotates within the upper housing 3. In this embodiment, the plate 63 rotates plus or minus 180 ° to minimize the amount the camera cable 21 is twisted. Full 360 degree rotation can easily be achieved by using conventional slip rings.
I S A zoom/focus motor 72 drives gears 73, 75, which rotate a zoom/focus shaft 77. The zoom/focus shaft extends downwardly through the right camera support 9. At the bottom of the focus shaft 77, a ring and pinion arrangement 79 transfers the rotary motion of the focus shaft 77 to a zoom lens mechanism (not shown) within the camera housing 5.
Referring now to Figure 17, the imaging device 1 is connected to a control console 20 101 by means of the imaging device cable 31. Signals from the CCD of the imaging device 1 are amplified by circuits in the control console 101 and directed to a display device 103. In one embodiment, the display device 103 is a conventional television set.
A foot pedal control assembly 105 allows the operator (not shown) to control the imaging device 1. The foot pedal control assembly 105 includes four controls (not shown):
35 ( 1 ) camera housing left and right; (2) camera housing up and down; (3) zoom in and out: and (4) light intensity up and down. Signals from the foot pedal control assembly 105 are routed to the control console 101. Circuits (not shown) in the control console 103 convert the control assembly signals into signals which are suitable to control the imaging device I. then route the converted signals to the imaging device I . It should be appreciated that the control 3o assembly 105 is not limited to implementation as a foot pedal control assembly. as numerous other control assemblies (examples of which are described above) can be employed.

In the embodiment shown in Figure 18, a computer 107 is interposed between the control console 101 and the display device 103. A plurality of computer programs contained in the computer 107 allow personnel to manipulate and/or store the signals from the imaging device 1.
Figures 19-21 illustrate a second imaging device which employs technology that can be employed to implement the embodiments of the present invention described above.
Referring first to Figure 19, the imaging device comprises two major assemblies: a camera assembly 150 and a disposable sheath assembly 152.
In the camera assembly 1 S0, a rotary stepper motor 154 is rigidly mounted in an upper to housing 156. A linear stepper motor 158 and the distal end of a planetary gear assembly 162 are press fitted in a linear stepper motor housing 164. The proximal end of the planetary gear assembly 162 is attached to the upper housing 156 by screws 168.
Three planetary gears 170 (only two of which are shown in Figure 19) are rotatably mounted on pins 172 within the planetary gear assembly 162. The rotary stepper motor 154 drives the planetary gears 170 through a sun gear 174.
The proximal end of a camera support tube 178 is press fitted in the linear stepper housing 164. A camera housing 180 is pivotally mounted between pair of arms I
82 (only one of which is shown in Figure I 0) that are integral with and extend from the distal end of the camera support tube 178. The linear stepper motor 158 acts through a pushrod 186 and a 2o fork 188 to control the elevation of the camera housing 180.
The sheath assembly 152 comprises a sheath 190, a sheath housing 192, and a ring gear 194. The distal portion of the sheath 190 is optically clear. The proximal end of the sheath 190 is adhesively attached within the distal end of the sheath housing 192. The ring gear 194 is adhesively attached within the proximal end of the sheath housing 192.
Prior to use, the camera assembly 1 ~0 is inserted into the sheath assembly 152, and the planet gears 170 engage the ring gear. As a result. when the rotary stepper motor 154 is actuated, the camera assembly 150 rotates in relation to the longitudinal axis 202 of the sheath assembly.
As is best shown in Figures 20 and 21, a CCD assembly 204 and a lens 206 are mounted 3o within a camera bore 208 in the camera housing 180. A pair of high intensity lights 210 are mounted in bores that are coaxial with the camera bore 208.

A mufti-conductor flexcable 212 provides the necessary connections for the CCD
assembly 204, for the camera housing lights 210, and for three high intensity lights 214, that are disposed in bores in the pushrod 186. The flexcable 212 extends from the camera housing 180 to the upper housing 156. In the upper housing 156, the flexcable 212 is combined with power and control wires (not shown) for the rotary stepper motor 154 and the linear stepper motor 158 to form the camera assembly cable 218. The camera assembly cable 218 passes through an orifice 220 in the upper housing I 56. As with the surgical/diagnostic device of Figures 11-18, the camera assembly cable 218 connects the camera assembly 150 to external display and control devices (not shown).
It should be appreciated that each of the embodiments of the present invention described herein is not limited to use solely in the aviation field, but may be used to image any inaccessible target. Moreover, the present invention is not solely limited to examining the engines of aircraft, as the present invention may be used to examine other portions of an aircraft, such as the hydraulic systems controlling flaps on the wings, the rudder control IS mechanisms, etc.
Having described several embodiments of the invention in detail. various modifications and improvements will readily occur to those skilled in the art.
Such modifications and improvements are intended to be within the spirit and scope of the invention. Accordingly, the foregoing description is by way of example only, and is not intended as limiting. The invention is limited only as defined by the following claims and the equivalents thereto.
It should be appreciated that each of the above-described embodiments of the present invention permits digital images of a region or regions of an aircraft to be generated and saved on conventional digital storage media. As a result, images generated by embodiments of the invention may be viewed in a location that is remote from the location where the inspection was performed, and may be transmitted electronically over a conventional communication network (e.g., the Internet). However, it should be appreciated that embodiments of the present invention are not limited to the use of an all digital system. In this regard. a coupling device may be provided for use with conventional borescopes and other types of imaging equipment. In particular. the techniques described in Applicant's co-pending U.S. Patent Application No. 09/064,542, filed on April 22, 1998, entitled COUPLING DEVICE FOR USE IN AN IMAGING SYSTEM. by the same Applicant, and incorporated herein by reference. may be used to generate a digital image from conventional analog equipment or even a traditional optical borescope.
What is claimed is:

Claims (15)

1. Aircraft inspection apparatus (200), comprising:
a first elongate support (221) having a proximal end and a distal end at opposite ends of a length axis wherein the distal end of the first support can be adjustably extended along the length axis away from the proximal end of the first support;
a light source (235) that is mounted to the distal end of the first support;
a camera (230) that is movably mounted to the distal end of the first support for movement, relative to the distal end of the first support, in rotation about the length axis of the first support; and means (260) for the remote control of the camera movement.

2. The aircraft inspection apparatus of claim 1, further comprising a second elongate support (211, 310)having a length axis, a distal end of which second support being mounted to the proximal end of the first support at an angle relative to the first support, the distal end of the first support being movable toward and away from the second support in a direction other than along the length axis of the second support.

3. The aircraft inspection apparatus of claim 1 or 2, further comprising a shaft (422, 622) that mounts the camera to the distal end of the first support, wherein the camera is movably mounted for rotation about the shaft.

4. The aircraft inspection apparatus of any one of the preceding claims, wherein the camera is movably mounted to the distal end of the first support for movement, relative to the proximal end of the first support, without altering a position of the proximal end of the first support.

5. The aircraft inspection apparatus of any one of the preceding claims, wherein the camera is pivotably mounted (622) to the distal end of the first support.

6. The aircraft inspection apparatus of any one of the preceding claims wherein the light source (235) is disposed adjacent the camera and mounted for movement together with the camera.

7. The aircraft inspection apparatus of any one of the preceding claims, wherein the camera is removably mounted to the distal end of the first support so that the camera can be replaced separately from the first support.

8. A method of inspecting inaccessible sites within a housing of an aircraft, comprising acts of:
selecting a first elongate support having proximal and distal ends spaced apart along a length axis, wherein the distal end can be adjustably extended along the length axis away from the proximal end;
inserting a camera and a light source that is mounted to the distal end of the first support into a portion of the aircraft, the camera being mounted for rotation about the length axis of the first support at a first position relative to the proximal end of the first support for viewing a first one of the inaccessible sites; and moving the camera by remote-control to a second position that is spaced apart from the first position, without changing a position of a proximal end of the first support, for viewing a second one of the inaccessible sites.

9. A method according to claim 8, further comprising the step of using a second elongate support, having proximal and distal ends spaced apart along a length axis and with the proximal end of the first support mounted to the distal end of second support such that the distal end of the first support can be moved towards and away from the second support in a direction other than along the length axis of the second support by changing the length of the first support, to advance the proximal end of the first support into said aircraft housing.

10. The method of claim 8 or 9, wherein the act of moving.
the camera includes moving the camera in a direction other than along a length axis of the first elongate support.

11. A method according to claim 8, 9 or 10, and further comprising:
telescoping the camera to the second position that is spaced apart from the first position.

12. The method of claim 11, further comprising an act of:
viewing images transmitted by the camera while remotely telescoping the first support.

13. A method according to any one of claims 8 to 12, further comprising:
illuminating the portion of the aircraft with a light source that moves with, and is disposed adjacent to, the camera.

14. A method according to any one of claims 8 to 13, further comprising:

generating from the camera a digital image of a portion of the aircraft;
transmitting the digital image of the portion of the aircraft to a storage device; and string the digital image on the storage device.

15. The method of claim 14, further comprising an act of:
transmitting the digital image to a location that is remote from a location of the aircraft.