GB2588432A

GB2588432A - Aircraft components

Info

Publication number: GB2588432A
Application number: GB1915387.3A
Authority: GB
Inventors: Tulloch William
Original assignee: Airbus Operations Ltd
Current assignee: Airbus Operations Ltd
Priority date: 2019-10-23
Filing date: 2019-10-23
Publication date: 2021-04-28
Also published as: GB201915387D0

Abstract

A component has a casing 122 around a body with a mounting 118, in use containing an image sensor 120 mounted to the body. The casing has a surface portion adapted to align with and/or form an external surface of an aircraft into which the component is mounted, with an optically transparent window through which the image sensor is aligned to capture images outside 126 the aircraft. The component may form a non-load bearing and/or a low category replaceable component of a wing section 102, with the surface portion forming a wing edge 104 and/or a wing-tip cap 116. A connection 130 to an aircraft power supply 134,132 may be provided for the image sensor. The sensor is preferably 360° to capture images of the surface around the aircraft. The window is preferably transparent to visible, infrared, x-ray and/or ultraviolet electromagnetic wavelengths. The surface portion may be formed from an aerospace-grade material such as perspex, acrylic, Norstar, glass or lexan polycarbonate.

Description

AIRCRAFT COMPONENTS

TECHNICAL FIELD

[0001] The present invention relates to an aircraft component that houses an image sensor. Particularly, but not exclusively, the component may be a wing component, which may be used instead of an existing wing component that does not house an image sensor.

BACKGROUND

100021 Aircraft typically have load bearing and non-load bearing parts. Non-load bearing parts may be modified or replaced without affecting the structural integrity of the aircraft. For example, the tip caps of an aircraft wing are usually non-load bearing and can be replaced without affecting the properties of the wing structure

SUMMARY

[0003] A first aspect of the present invention provides a component for mounting on or in an aircraft. The component comprising a body containing a mounting for mounting an image sensor; and a casing around the mounting to contain a mounted image sensor when in use. The casing comprises an surface portion adapted to align with and/or form an external surface of an aircraft into which the component is to be mounted, the surface portion comprising an optically transparent window portion through which the image sensor when mounted is aligned to capture images outside of the aircraft. This may provide an additional space for the installation of optical devices, be it additional lights or optical sensors, such as cameras.

[0004] Optionally, the component forms a non-load bearing component of a wing section Therefore, the component may not be required to conform to the same standards as load bearing components.

[00051 Optionally, the component may form a low category component of a wing section.

[0006] Optionally, the surface portion forms an edge portion of a wing section. This may provide a position to mount an image sensor with an unobstructed view of at least a portion of the external area and surface area of the aircraft.

100071 Optionally, the component forms a tip cap of the wing. The tip cap is in a prominent position yet has a relatively low risk of damage from collisions. As such, an image sensor mounted in a wing tip has a wide field of view both towards and away from the respective aircraft.

100081 Optionally, the component may comprise a power connector to connect a mounted image sensor within the casing to a power supply contained within the aircraft. This power connector may allow the image sensor mounted in the casing to be connected to the existing power system thus minimising the need to redesign the power network to accommodate an image sensor.

100091 Optionally, the image sensor when mounted is aligned to capture images around the aircraft and/or of a surface of the aircraft. Such fields of vision may allow the presence of an external unmanned aircraft and/or surface damage to be detected.

100101 Optionally, the image sensor is a 3600 degree image sensor, These image sensors may capture images with a wider field of vision.

100111 Optionally, the optically transparent window portion is transparent to any, or a combination of: visible, infrared, near infrared, x-ray, and ultraviolet electromagnetic wavelengths. This may allow images to be captured across a wide portion of the electromagnetic spectrum.

100121 Optionally, the surface portion comprises an aerospace-grade material, such as any, or a combination of: Perspex, acrylic, Norstar, glass, lexan polycarbonate 100131 Optionally, the component comprises an image sensor.

100141 A second aspect of the present invention provides a replacement component comprising a component according to the first aspect. This may allow existing aircraft to be retrofitted with such components [0015] A third aspect of the present invention provides an aircraft section comprising an external surface and an image sensor mounted within the section and beneath the external surface, the external surface comprising an optically transparent window portion through which the image sensor is aligned to capture images outside of the aircraft.

[0016] A fourth aspect of the present invention provides an aircraft with a component according to the first aspect of the present invention or a replacement component according to the second aspect of the present invention.

[0017] A fifth aspect of the present invention provides a method of modifying an aircraft comprising replacing a portion of a section of the aircraft with a replacement component according to the second aspect of the present invention.

[0018] Optionally, the method may form an electrical connection between the replacement wing component and an existing power line of the aircraft wing section, to power the image sensor when mounted and in use. This provides power to any image device or sensor mounted within the casing of the wing component.

BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Embodiments of the invention will now be described, by way of example only, with reference to the accompanying drawings, in which: [0020] Figure 1 is a schematic diagram of a part of a wing tip, according to an example; [0021] Figure 2 is a schematic diagram of the wing tip of Figure I, with the tip cap removed, and illustrating a replacement tip cap, according to an example, [00221 Figure 3 is a schematic diagram of the wing tip of Figure 2 with the replacement tip cap installed, according to an example; 100231 Figure 4 comprises three schematic diagrams, A, B, and C, of an alternative wing tip and showing a replacement tip cap, according to another example.

[0024] Figure 5a is a schematic diagram of an aircraft power connection according to an example; [0025] Figure 5b is a schematic diagram of a power system according to an example, and [0026] Figure 6 is a schematic diagram of a power connector according to an example.

DETAILED DESCRIPTION

[0027] Examples herein relate generally to parts or components of an aircraft. The parts or components may be designed and built on or in an original aircraft or may replace original parts or components. In particular non-limiting examples herein, the parts or components replace parts of an aircraft wing. However, in other examples, the parts or components could form or replace other aspects of an aircraft, such as vertical or horizontal stabilisers, or any other areas of an aircraft, as will be appreciated.

[0028] Figure 1 is a schematic diagram 100 of a section of an aircraft wing 102, according to an example. The wing section comprises a leading edge 104, a trailing edge 106, a wing tip end 108, a fuselage end 110; an outer surface 112 and a tip cap 114. The leading edge 104 is the first part of the aircraft wing 102 that contacts the air and as such has an aerodynamic profile. The tip cap 114 forms part of the leading edge 104 and is a non-load bearing component. Tip caps are typically constructed of machined aluminium to be connected to the wing tip end 108.

[0029] An example of a component, which in this instance is a replacement wing tip cap 116, is shown in Figure 2 and Figure 3, which illustrates the same wing section as Figure 1. Figure 2 shows the wing 102 without the original tip cap 114. Figure 3 shows the replacement tip cap 116 fitted to the wing 102, according to an example.

[0030] The tip cap 116 comprises a body containing a mounting 118 and, mounted thereon, an image sensor 120. The image sensor is enclosed within the body of the tip cap 116 by a casing 122. As shown the casing 122 is shaped to fit the aerodynamic profile of the surface of the wing. In other words, in this example, the casing has the same external shape and profile as the replaced tip cap 114. The casing 122 is adapted to align with and form part of the existing leading edge 104 of the wing section 102. The tip cap 116 comprises an optically transparent window portion through which the image sensor 120 is positioned and/or aligned to capture images outside 126 of the aircraft wing section 102. In this example, the image sensor 120 has a field of view encompassing the outside area and the surface of the aircraft.

[0031] The image sensor 120 is powered via a power cable 128 and a plug connector 130, which connects to an existing power line 132 of the aircraft wing 102 via a power unit arrangement 134 including a respective socket for the plug connector 130. The power unit H4 is described in more detail hereafter with reference to Figure 5a, 5b and 6. In one example, the plug connector 130 is a standard male USB connector, for example a male USB-A connector, and the socket is a female USB-A connector. Other configurations and kinds of plug/socket may of course be used instead. However, a standard USB connection arrangement is convenient for use with mainstream, commercially-available image sensors and cameras.

[0032] The optically transparent window may form part of the casing 122, or the casing 122 may be optically transparent itself The optically transparent window may be composed of a material to withstand the conditions that the aircraft may experience when in flight. Some example materials may comprise any, or a combination of PerspexTM, acrylic, NorstarTM, glass, LexanTM polycarbonate or other optically transparent material. Moreover, the material of the window may be optically transparent to any, or a combination of: visible, infrared, near infrared, x-ray, and ultraviolet electromagnetic wavelengths. This allows different image sensors 120 to be used if required.

[0033] Figure 4 shows three schematic diagrams, A, B, and C, of a wing tip end 140 according to another example. The wing tip end 140 has similar features to the foregoing example and like reference numerals represent the like features. View A shows the wing tip end 140 with the tip cap 114 forming part of an upper leading edge 104. View B shows the same wing tip 140 with the tip cap 114 removed from the upper leading edge 104. View C shows the replacement tip cap 116 fitted to the wing tip end 140 and forming part of the upper leading edge 104.

[0034] The tip end 140 is curved upward and is a near vertical extension of the wing. Thus, the tip cap 114, 116 is located in a position that has a reduced likelihood of damage in the event of potential collisions with debris or other objects, for example, while taxiing. By replacing the existing tip cap 114 with tip cap 116, or by manufacturing an aircraft with the tip cap 116, an image sensor 120 located within the tip cap 116 is in a relatively 'low risk' position. The image sensor 120 mounted within the tip cap 116 may indeed be controllable to record any such collisions or may be able to detect the presence of the resultant surface damage [0035] An example of a power unit arrangement 134 to power an image sensor according to examples herein is described with reference to Figures 5a and 5b The power unit arrangement 134 may be an existing power system or a purpose-designed system. According to one example, the power system comprises an existing power line 132, which terminates with a first power connector 136, which ordinarily couples into a second power connector 151 of an existing power supply unit 152. As illustrated in Figure 5a, however, an intervening adaptor, in the form of an inline power connector 150, is introduced inline in between the first power connector 136 and the second power connector 151. Figure 5b shows the first, second and inline power connectors in a connected or coupled configuration.

[0036] As shown, the inline power connector 150 is located between the other power connectors 136, 151 and is adapted to tap or draw-off a fraction of the power, via an appropriate connector (such as a USB connector), into a power cable 128, which connects to and powers the image sensor.

[0037] As has already been described, the inline power connector 150 comprises circuitry to convert an operating voltage of the aircraft to an operating voltage suitable for powering the image sensor 120. The circuitry may convert DC-DC or AC-DC, and may include voltage step-down capability, depending on the rating of the existing power line 132 and power supply 152. Circuits for regulating, converting, rectifying and/or stepping-down voltages are well-known and may be realised inside of the inline power connector] 50 in a convenient chip package.

[0038] Figure 6 is a more detailed schematic diagram of an example of a power adaptor such as an inline power connector 150. The inline power connector 150 comprises a male connector 153 and a female connector 154. The male connector 153 has the same form as the first connector 136 and the female connector 154 has the same form as the second connector 151. The power connector 150 is adapted to fit 'in-line' with the existing power system, between the power cable 132 and the power supply unit 152. In this example, the female connector 154 connects to the existing power line 132 via the first connector 136 and the male connector 153 connects to the power supply unit 150 via the second connector 151. Other examples may, of course, apply a different arrangement of male and/or female connectors to facilitate the introduction of an inline power connector 150.

[0039] Although not shown, the inline power connector 150 also comprises pass-through circuitry and/or wiring to pass power from the power line 132 to the power supply 152 in an uninterrupted manner.

[0040] In the example shown in Figure 6, the inline power connector ISO comprises two USB ports 156 and 158, to provide power to one or more image sensors or, indeed, other ancillary devices via an appropriate lead. In this way, power can be provided to image sensors mounted in a tip cap by adapting and using existing power systems. An inline connector of the kind described herein simplifies the installation of such devices and avoids or at least mitigates the need to re-design existing power systems and harnesses.

In other examples, ports other than USB ports may be provided and/or circuitry may be adapted to convert a power supply as required. In addition, there may only be one connection port, or more than two as shown in the example 150 [0041] An image sensor as described herein may have a wide or a panoramic field of view, for example greater than 160° horizontally and/or greater than 75° vertically. What each image sensor can see for any given field of view is of course dictated by where the image sensor is mounted on the aircraft and in which direction it is directed. At least one of the image sensors may have a 360° field of view horizontally and 90° or greater vertically. Image sensors may be fixed, for example as applied in catadioptric cameras, and derive their wide fields of view from fixed elements, such as lenses or mirrors. Other image sensors may be movable, such as rotatable, to achieve their fields of view. Such image sensors may be aligned to capture images around the aircraft or of the aircraft. Some image sensor, such as 360° image sensors, may be arranged to capture images of the aircraft and of the space around the aircraft. In any case the image sensors may be connected to and be in communication with a central processor (not shown) via an appropriate wireless access point (not shown). Connectivity may use a wireless protocol, such as an Internet of Things (IoT) protocol such as Bluetooth, WiFi, Ziz,Bee, MQTT IoT, CoAP, DSS, NEC, Cellular, AMQP, RFID, Z-Wave, EnOcean and the like. The wireless connection may be used to communicate control instructions from the central processor to the image sensor and to pass back image data from the image sensor 120 to the central processor. In this way, there is no need to introduce or extend a wired/fibre data network into extremities of an aircraft fuselage or wings, where it is unlikely such a communications infrastructure, which is easy to tap into, already exists.

[0042] It is to be noted that the term "or" as used herein is to be interpreted to mean "and/or", unless expressly stated otherwise. The description is in relation to a tip cap of a wing and it will be appreciated that any other component of the wing could equally be used. Such as sections of the leading edge, other sections of the wing surface, or the leading edge of the vertical and horizontal stabilisers.

Claims

CLAIMS: 1 A component for mounting on or in an aircraft, the component comprising: - a body containing a mounting for mounting an image sensor; and - a casing around the mounting to contain a mounted image sensor when in use, the casing comprising a surface portion adapted to align with and/or form an external surface of an aircraft into which the component is to be mounted, the external surface portion comprising an optically transparent window portion through which the image sensor when mounted is aligned to capture images outside of the aircraft.
2. A component according to claim 1, for forming a non-load bearing component of a wing section.
3. A component according either preceding claim, for forming a low category component of a wing section.
4 A component according to any one of the preceding claims, wherein the surface portion forms an edge portion of a wing section.
5. A component according to any one of the preceding claims, for forming a tip cap of a wing tip of a wing
6. A component according to any one of the preceding claims, comprising a power connector to connect a mounted image sensor within the casing to a power supply contained within the aircraft.
7. A component according to any one of the preceding claims, wherein the image sensor when mounted is aligned to capture images around the aircraft.
8. A component according any one of the preceding claims, wherein the image sensor when mounted is aligned to capture images of a surface of the aircraft.
9 A component according to any one of the preceding claims, wherein the image sensor is a 3600 degree image sensor.
10. A component according to any one preceding claim, wherein the optically transparent window portion is transparent to any, or a combination of: visible, infrared, near infrared, x-ray, and ultraviolet electromagnetic wavelengths.
11. A component according to any one preceding claim, wherein the surface portion comprises an aerospace-grade material.
12. A component according to any one of the preceding claims, wherein the surface portion comprises any, or a combination of: Perspex, acrylic, Norstar, glass, or lexan polycarbonate.
13. A component according any one of the preceding claims further comprising a mounted image sensor.
14. A replacement component comprising a component according to any one of the preceding claims.
An aircraft section comprising an external surface and an image sensor mounted within the section and beneath the external surface, the surface comprising an optically transparent window portion through which the image sensor is aligned to capture images outside of the aircraft.
16. An aircraft comprising a component according to any one of claims 1 to 13, a replacement component according to claim 14 or an aircraft section according to claim 15
17. A method of manufacturing or modifying an aircraft comprising replacing a component with a replacement component according to claim 14.
18. A method according to claim 17, comprising forming an electrical connection between the replacement component and an existing power line of the aircraft section, to power the image sensor when mounted and in use