DE102019120177A1 - Camera system for aircraft and aircraft - Google Patents

Abstract

The invention relates to a camera system (1) for aircraft (F), in particular an aircraft camera system (2) comprising a cover (4) and a camera. The camera system (1) further comprises a base plate (3), the camera (5) being physically divided into an image sensor element (6) that provides raw data and a controller (7), the camera system (1) means for data transmission (8) comprises, by means of which the image sensor element (6) and the controller (7) are connected for transmitting the raw data, the camera system (1) comprising means for energy transmission (9) by means of which the image sensor element (6) is supplied with electrical energy, wherein the camera system (1) further comprises an adapter (18) with which the image sensor element (6) is held on the base plate (3), the cover (4) and the adapter (18) being designed in this way and on which the base plate (3 ) are arranged that an aerodynamic body (11) is formed which covers the base plate (3) are connected to one another to form a receiving housing (11), wherein in the aerodynamic body (11) a relative to an environment (U) The closed receiving space (12) is formed, the image sensor element (6) being arranged inside the receiving space (12) and the controller (7) being arranged outside the receiving space (12).

Description

The invention relates to a camera system for aircraft and an aircraft according to the preamble of claims 1 and 13, respectively.

From the DE 34 17 917 C2 a camera system for an aircraft is known which comprises a cover and a camera.

It is the object of the invention to propose a camera system for an aircraft by means of which at least one camera can be arranged in a highly flexible position on an aircraft. Another object of the invention is to propose an aircraft on which at least one camera is arranged in a highly flexible position.

This object is achieved on the basis of the features of the preamble of claim 1 and 13 by the characterizing features of claim 1 and 13, respectively. Advantageous and expedient developments are specified in the respective sub-claims.

The camera system according to the invention for aircraft, which is designed in particular as an aircraft camera system, comprises a cover, a camera and a base plate, the camera being physically divided into an image sensor element providing raw data and a controller, the camera system comprising means for data transmission by means of which the image sensor element and the controller are connected to transmit the raw data, the camera system comprising means for power transmission by means of which the image sensor element is supplied with electrical energy, the camera system further comprising an adapter with which the image sensor element is held on the base plate, the cover and the adapter are designed and arranged on the base plate in such a way that an aerodynamic body is formed which covers the base plate and wherein a receiving space that is closed off from an environment is formed in the aerodynamic body, and wherein the image sensor element is arranged inside the receiving space, and wherein the controller is arranged outside the receiving space. Because only the most necessary components are arranged in the aerodynamic body, the volume of the aerodynamic body can be kept small, so that aerodynamic disturbances are minimized.

Furthermore, it is provided that the means for data transmission are either designed as a data transmission line or as a wireless data transmission device, by means of which the image sensor element is connected to the controller for data transmission and the means for energy transmission are either designed as an energy supply line or as a wireless energy transmission device by means of which the image sensor element is connected to electrical energy is supplied. A wired configuration of the means for data transmission and the means for energy transmission makes it technically easy to equip an aircraft and it also does not have to be taken into account to what extent an outer skin of the aircraft permits wireless communication and wireless energy transmission. A wireless design of the means for data transmission and the means for energy transmission makes it possible to equip aircraft so that complete equipment of the aircraft with the camera system is simplified and the number of processing steps to be carried out on the aircraft is reduced.

It is also provided to equip the base plate with an opening, the data transmission line and / or the power supply line being guided through this opening and being sealed off from the base plate by a sealing means. This reliably prevents liquid or moisture from penetrating into the aircraft.

It is also provided that the base plate is designed with a spherically curved upper side. As a result, the image sensor element can also be arranged in different orientations with regard to its elevation angle and its side angle, so that a horizontal orientation of the image sensor element is possible even with a base plate mounted at an angle.

Furthermore, it is provided that the adapter is designed as a housing and that the image sensor element is accommodated in an interior of the housing and the housing is fastened on an upper side of the base plate, the adapter optionally in a first position or in at least any other position, which differs from all other positions, is attached to the top of the base plate. In this way, the image sensor element can be optimized in a technically simple manner for attachment to the base plate. The housing can be designed as a hermetically sealed housing. This protects the image sensor element from the ambient conditions and in particular from cold and moisture.

It is also provided that the data transmission line and / or the power supply line of the camera system are each designed as a multi-pole line and each is equipped with a multi-pole coupling means, the coupling means comprising a first coupling part and a second coupling part, the Coupling parts are designed in particular as a plug connection or as a twist-plug connection.

This makes it possible to uncouple the image sensor element together with a first half of the connecting line connected to it, which includes the first coupling part, and to remove it from the receiving space, for example for maintenance purposes. It is also possible to reinstall the serviced image sensor element or another image sensor element in the recording space.

Provision is also made for the first coupling means and / or the second coupling means to be arranged in the receiving space. The particular advantage here is that a second cable half, which includes the second coupling part, does not have to be separated from the base plate when the image sensor element is removed together with the first cable half.

It is also provided that the cover is screwed to the base plate. This enables quick access to the image sensor element located in the recording space. In particular, it is provided that the cover can be both assembled and disassembled without tools or with a standard tool. This turns the image sensor element into a Line Replaceable Unit, or LRU for short. In aviation, a technical unit is referred to as an LRU if it can be changed while the scheduled service is running without the usual flight operations being restricted and the change taking a maximum of around 15 minutes without the need for special tools.

Finally, it is also provided that the camera comprises at least one further image sensor element and that the camera system comprises at least one further adapter, the further image sensor element being arranged on the further adapter and the further adapter being part of the aerodynamic body. This creates a camera system which has particularly large viewing angles, in particular of more than 180 °, or which delivers a forward and a backward image or a left and right image or an all-round image. This allows the number of camera systems required for comprehensive observation of an airfield to be significantly reduced.

It is also provided that the wireless data transmission device comprises a first data transmission and reception device and a second data transmission and reception device, wherein the first data transmission and reception device is connected to the controller and outside the receiving space either remotely from the base plate or is arranged on the base plate and wherein the second data transmitting and receiving device is connected to the image sensor element and is arranged either outside the receiving space under the base plate or in the receiving space on the base plate or on the adapter. With an appropriate arrangement, the camera system can be easily assembled, disassembled and maintained.

It is also provided that the wireless energy transmission device comprises an energy transmission device and an energy reception device, wherein the energy transmission device is arranged outside of the receiving space either remotely from the base plate or on the base plate and wherein the energy reception device is connected to the image sensor element and is arranged either in the receiving space on the base plate or in the receiving space on the adapter or in the receiving space on the image sensor element or outside the receiving space on the base plate. With an appropriate arrangement, the camera system can be easily assembled, disassembled and maintained.

Furthermore, it is provided to equip the camera system with at least one further sensor different from the image sensor element, the further sensor being arranged in the recording space and preferably connected to the controller via the means for data transmission and the means for energy transmission. In this way, the camera system can be equipped with additional sensors in a simple manner, since the additional sensor only has to be inserted into the aerodynamic body and connected to the means for data transmission and the means for energy transmission. It is also provided that the camera system in the recording space includes at least one multi-pole connection to which the additional sensor for data transmission and / or energy transmission is connected.

In the aircraft according to the invention, provision is made for the aircraft to be equipped with at least one camera system according to at least one of claims 1 to 12. Because the camera system is designed in such a way that only the most necessary components of the camera system are arranged in the aerodynamic body, the volume of the aerodynamic body can be kept small, so that aerodynamic disturbances caused by it are minimized. Furthermore, with the camera system it is possible to arrange the controller of the camera system protected from environmental influences in an interior volume of the aircraft within an aircraft skin, so that the technical requirements that the controller must meet are lower than if it were arranged outside the aircraft skin.

It is also provided that the aircraft includes a pressurized cabin and that the controller of the camera system is arranged within the pressurized cabin. As a result of this measure, the technical requirements that are placed on the controller, for example with regard to a temperature range in which it works reliably, are lower and the controller is therefore also more cost-effective.

It is provided that the aircraft comprises wings, a tail unit and a fuselage, the aerodynamic body being fastened with its base plate to one of the wings or to the tail unit or to the fuselage. Such an arrangement allows areas to be monitored in a simple manner which are not visible to the pilots from the cockpit.

It is also provided that the first data transmission and reception device is arranged under an outer skin of the aircraft and below the base plate or that the first data transmission and reception device is arranged above an outer skin of the aircraft and is covered by the base plate. Both arrangement variants enable the aircraft to be pre-equipped at suitable points on the fuselage or the wings or the tail unit.

Finally, provision is made to arrange the energy transmission device under an outer skin of the aircraft and below the base plate, or to arrange the energy transmission device over an outer skin of the aircraft and cover it with the base plate. In both arrangement variants, the energy transmission device is protected from the effects of the weather.

For the purposes of the invention, a controller of the camera system is to be understood as a functional unit in which the raw data made available by the image sensor element is converted into a compressed video or image format and transferred to a wireless or wired interface for transmission to at least one downstream electronic device such as for example a monitor or a memory or a forwarding device, in particular a transmitter or an image evaluation and image analysis device, can be provided.

Further details of the invention are described in the drawing on the basis of exemplary embodiments shown schematically.

• 1: eine schematische Frontansicht eines erfindungsgemäßen Kamerasystems;
• 2: eine schematische Seitenansicht von rechts auf das in der 1 gezeigte Kamerasystem;
• 3: eine schematische Draufsicht auf das in den 1 und 2 gezeigte Kamerasystem;
• 4: eine geschnittene Seitenansicht eines mit einer Kamera bestückten Adapters des in den 1 bis 3 gezeigten Kamerasystems,
• 5: eine schematische Draufsicht auf ein erfindungsgemäßes Flugzeug, an welchem das erste Kamerasystem und drei weitere Kamerasysteme verbaut sind,
• 6a-e: schematische Ansichten je eines Details von fünf weiteren, erfindungsgemäßen Flugzeugen und fünf darin exemplarisch verbauter erfindungsgemäßen Kamerasystemen, bei welchen die Mittel zur Datenübertragung und die Mittel zur Energieübertragung unterschiedlich angeordnet sind, und
• 7-9: drei weitere erfindungsgemäße Kamerasysteme.

Here shows:

• 1 : a schematic front view of a camera system according to the invention;
• 2 : a schematic side view from the right of that shown in FIG 1 camera system shown;
• 3 : a schematic plan view of the in the 1 and 2 camera system shown;
• 4th : a sectional side view of an adapter equipped with a camera of the in the 1 to 3 shown camera system,
• 5 : a schematic top view of an aircraft according to the invention, on which the first camera system and three further camera systems are installed,
• 6a-e : schematic views each of a detail of five further aircraft according to the invention and five camera systems according to the invention built therein by way of example, in which the means for data transmission and the means for energy transmission are arranged differently, and
• 7-9 : three further camera systems according to the invention.

In the 1 Figure 3 is a front view of a camera system according to the invention 1 shown. The 2 FIG. 13 shows a right side view of that in FIG 1 camera system shown 1 . The 3 FIG. 13 shows a schematic plan view of the one in FIG 1 and 2 camera system shown 1 . The camera system 1 is for installation in or attachment to the 1 and 2 excerpts and in the 5 aircraft shown in a schematic plan view F. provided and accordingly forms an aircraft camera system 2 . The camera system 1 includes a base plate 3 , a cover 4th and a camera 5 . In the 1 and 2 is under the base plate 3 schematically in each case a section of an outer skin AH of the aircraft F. shown. The camera 5 comprises an image sensor element 6 and a controller 7th and is physically in the image sensor element providing raw data 6 and the image sensor element processing the raw data 6 controlling controller 7th divided up. The camera system 1 includes funds 8th for data transmission by means of which the image sensor element 6 and the controller 7th are connected to transfer the raw data. The camera system also includes 1 medium 9 for energy transfer, by means of which the image sensor element 6 with electrical energy from an energy source 10 is supplied. The cover 4th and the base plate 3 are such an aerodynamic body 11 interconnected that one opposite an environment U closed recording room 12th is formed. The image sensor element 6 is inside the recording room 12th arranged and the controller 7th is outside the recording room 12th arranged.

The means 8th for data transmission are as a data transmission line 13 formed, by means of which the image sensor element 6 with the controller 7th is connected for data transmission. The means 9 for power transmission are as power supply lines 14th formed, by means of which the image sensor element 6 from the energy source 10 which are outside the recording room 12th is arranged, is supplied with electrical energy. This includes the base plate 3 an opening 15th , the data transmission line 13 and / or the power supply line 14th through this opening 15th is guided and opposite the base plate 3 by a sealant 16 which is only available in the 1 is shown is sealed.

To the image sensor element 6 in the recording room 12th to be able to align individually and a field of vision 17th of the image sensor element 6 which is only available in the 2 is shown to be able to optimally adapt to the requirements, has the base plate 3 a spherically curved top 3a on.

For optimal handling of the image sensor element 6 it is provided that the camera system 1 an adapter 18th comprises, wherein the image sensor element 6 using the adapter 18th on the top 3a the base plate 3 is attached. The adapter 18th is as a housing 27 formed and the adapter 18th is in one in the 1 to 3 shown first position P18-1 on the top 3a the base plate 3 attached. It is also possible to use the adapter 18th in any other positions on the top 3a the base plate 3 to fix. Another position is in the 3 with dashed lines a second position as an example P18-2 indicated.

The data transmission line 13 and the power supply line 14th of the camera system are each designed as a multi-pole line and each include a multi-pole coupling means 19th or. 20th . The coupling agent 19th the data transmission line 13 comprises a first coupling part 19a and a second coupling part 19b , the coupling parts 19a , 19b are designed as a plug connection. Alternatively, a design as a turn-plug connection is also provided. The coupling agent 20th the power supply line 14th comprises a first coupling part 20a and a second coupling part 20b , the coupling parts 20a , 20b are designed as a plug connection. Alternatively, a design as a turn-plug connection is also provided.

According to an embodiment variant not shown, it can also be provided to combine the data transmission line and the power supply line and to provide a common coupling means so that both lines can be coupled or uncoupled with one movement.

The coupling agents 19th , 20th are in the recording room 12th arranged. This makes it possible after removing the cover 4th from the base plate 3 the image sensor element 6 or the image sensor element 6 and the adapter 18th by uncoupling the coupling means 19th and 20th from the recording room 12th to be removed and exchanged, for example, in the event of service.

In particular for maintenance purposes, it is provided that the cover 4th with the base plate 3 is screwed. In the exemplary embodiment shown, this is done using four screws 21a , 21b , 21c , 21d, which through in the cover 4th trained channels K21a , K21b , K21c , K21d are guided and in thread 22a , 22b , 22c , 22d grip that in the base plate 3 are trained. See also 3 . In the 1 is shown as an example that the base plate 3 by means of screws S3-1 and S3-2 with the outer skin AH of the aircraft F. is screwed. Alternatively, provision can also be made for the base plate to be glued to the outer skin of the aircraft or to be fixed to the aircraft using other fastening methods.

According to one embodiment, it is also provided that the camera 5 comprises two image sensor elements. This is in the 3 shown as an example. Here is the mentioned image sensor element 6 shown. There is also a second image sensor element 23 indicated, which in contrast to the forward in the direction of the arrow x aligned first image sensor element 6 up in the direction of the arrow z (see regarding the direction of the arrow z also 2 ) is aligned.

An example and schematic is shown in 3 another embodiment indicated in which a further sensor 24 is included, which has different properties from an image sensor. The other sensor 24 is in the recording room 12th on the side of the adapter 18th arranged and by means of an adapter cable set 25th to the available funds 8th for data transfer and the available means 9 for energy transfer and thus to the controller 7th and the energy source 10 connected. The means 8th for data transfer and the available means 9 for energy transfer are in the 1 and 3 shown only schematically, this being in the 1 completely and in the 3 are also only partially shown.

In the 4th are a partially sectioned plan view of the adapter 18th with the image sensor element 6 shown. The one as a housing 27 trained adapters 18th includes a hermetically sealed interior 26th . The housing also includes 27 of the adapter 18th a breakthrough 28 , which through a transparent pane 29 is closed, behind which the image sensor element 6 is arranged.

The one in the 1 to 4th camera system shown 1 is the image sensor element 6 the camera 5 in the recording room 12th of the aerodynamic body 11 inside the adapter 18th , namely in the interior 26th of the adapter 18th arranged.

In the 5 is a schematic plan view of the aircraft mentioned F. shown. The camera system described is on this 1 on a first wing F1 installed. Furthermore is on the aircraft F. on a second wing F2 , at a first end F3 and at a second end F4 of a tailplane CPR of a tail unit LW one more for the camera system 1 identical camera system 92 , 93 , 94 installed. It can also be provided on a vertical tail unit SLW of the tail unit LW to arrange at least one further camera system.

The following is in relation to the 5 only the first camera system 1 described and illustrated in more detail. The second to fourth camera system 92 , 93 , 94 is carried out analogously. The plane F. includes in a fuselage R. a pressurized cabin DK . The controller 7th and the energy source 10 of the camera system 1 are inside the pressurized cabin DK arranged. Also in the 1 is the pressurized cabin DK indicated schematically.

The 6a to 6e show in a schematic view details of further five aircraft according to the invention F100 , F200 , F300 , F400 , F500 and five camera systems according to the invention built onto them as examples 101 , 201 , 301 , 401 , 501 which each have a base plate 103 , 203 , 303 , 403 , 503 , an adapter 118 , 218 , 318 , 418 , 518 , a cover 104 , 204 , 304 , 404 , 504 and a camera 105 , 205 , 305 , 405 , 505 , Means of data transmission 108 , 208 , 308 , 408 , 508 and means of energy transmission 109 , 209 , 309 , 409 , 509 include. Here, the means for data transmission and the means for power transmission are partially arranged and designed differently. The camera system 101 , 201 , 301 , 401 , 501 is as an aircraft camera system 102 , 202 , 302 , 402 , 505 educated.

Here is the camera 105 , 205 , 305 , 405 , 505 each physically in an image sensor element that delivers raw data 106 , 206 , 306 , 406 , 506 and a controller 107 , 207 , 307 , 407 , 507 split, with the camera system 101 , 201 , 301 , 401 , 501 the means for data transmission 108 , 208 , 308 , 408 , 508 comprises, by means of which the image sensor element 106 , 206 , 306 , 406 , 506 and the controller 107 , 207 , 307 , 407 , 507 are connected to the transmission of the raw data, the camera system 101 , 201 , 301 , 401 , 501 in each case the means of energy transmission 109 , 209 , 309 , 409 , 509 comprises, by means of which the image sensor element 106 , 206 , 306 , 406 , 506 is supplied with electrical energy. Here form the cover 104 , 204 , 304 , 404 , 504 and the adapter 118 , 218 , 318 , 418 , 518 on the base plate 103 , 203 , 303 , 403 , 503 an aerodynamic body 111 , 211 , 311 , 411 , 511 , being in the aerodynamic body 111 , 211 , 311 , 411 , 511 one versus one environment U closed recording room 112 , 212 , 312 , 412 , 512 is trained. Here is the image sensor element 106 , 206 , 306 , 406 , 506 each within the recording room 112 , 212 , 312 , 412 , 512 arranged and here is the controller 107 , 207 , 307 , 407 , 507 each outside of the recording room 112 , 212 , 312 , 412 , 512 arranged. The image sensor element 106 , 206 , 306 , 406 , 506 is by means of the adapter 118 , 218 , 318 , 418 , 518 on top of the base plate 103 , 203 , 303 , 403 , 503 attached. According to an embodiment variant not shown, it can also be provided that the adapter is designed as a housing and that this forms an interior space that is closed off from the environment in the receiving space, so that the image sensor element is already adequately protected by the adapter housing and the cover is next to an aerodynamic one The cladding only provides additional protection. With such a design of the adapter housing, the image sensor element remains fully functional even if the cover is damaged or missing.

With all five camera systems 101 , 201 , 301 , 404 , 501 are the means 108 , 208 , 308 , 408 , 508 for data transmission as a wireless data transmission device 113 , 213 , 313 , 413 , 513 formed, by means of which the image sensor element 106 , 206 , 306 , 406 , 506 with the controller 107 , 207 , 307 , 407 , 507 is connected for data transmission. With all five camera systems 101 , 201 , 301 , 404 , 501 are the means of energy transfer 109 , 209 , 309 , 409 , 509 as a wireless energy transmission device 114 , 214 , 314 , 414 , 514 formed, by means of which the image sensor element 106 , 206 , 306 , 406 , 506 each from one energy source 110 , 210 , 310 , 410 , 510 is supplied with electrical energy.

This includes the wireless data transmission device 113 , 213 , 313 , 413 , 513 a first data transmitting and receiving device 119a , 219a , 319a , 419a , 519a and a second data transmitting and receiving device 119b , 219b , 319b , 419b , 519b .

The first data sending and receiving device 119a , 219a , 319a , 419a , 519a is to the controller 107 , 207 , 307 , 407 , 507 connected and outside a recording room 112 , 212 , 312 , 412 , 512 either removed from the base plate 103 , 203 , 403 , 503 (please refer 6a , 6b , 6d , 6e) or on the base plate 303 (please refer 6c ) arranged. The second data sending and receiving device 119b , 219b , 319b , 419b , 519b is to the image sensor element 103 , 206 , 306 , 406 , 506 connected and either outside the recording room 112 , 212 under the base plate 103 , 203 ( please refer 6a , 6b) or in the recording room 312 , 412 , 512 on the base plate 303 , 403 , 503 (please refer 6c , 6d , 6e) or alternatively and not shown arranged on the adapter.

The wireless energy transmission device 114 , 214 , 314 , 414 , 514 comprises an energy transmitter 120a , 220a , 320a , 420a , 520a and an energy receiving device 120b , 220b , 320b , 420b , 520b . The energy transmission device 120a , 220a , 320a , 420a , 520a is outside the recording room 112 , 212 , 312 , 412 , 512 either removed from the base plate 103 , 203 , 403 , 503 (please refer 6a , 6b , 6d , 6e) or on the base plate 303 (please refer 6c ) arranged. The energy receiving device 120b , 220b , 320b , 420b , 520b is to the image sensor element 103 , 203 , 306 , 406 , 506 connected and either in the recording room 312 , 412 , 512 on the base plate 303 , 403 , 503 (please refer 6c , 6d , 6e) or according to an embodiment variant not shown in the receiving space on the adapter or according to a further embodiment variant not shown in the receiving space on the image sensor element or outside the receiving space 112 , 212 on the base plate 103 , 203 (please refer 6a , 6b) arranged.

The same applies to aircraft F100 , F200 , F300 , F400 , F500 the first data transmitting and receiving device 119a , 219a , 419a , 519a under an outer skin AH100 , AH200 , AH400 , AH500 of the aircraft F100 , F200 , F400 , F500 and below the base plate 103 , 203 , 403 , 503 arranged (see 6a , 6b , 6d , 6e) or the first data transmitting and receiving device 319a is over the outer skin AH300 of the aircraft F300 arranged and through the base plate 303 covered (see 6c ).

The same applies to aircraft F100 , F200 , F300 , F400 , F500 the energy transmitting device 120a , 220a , 420a , 520a under the outer skin AH100 , AH200 , AH400 , AH500 of the aircraft F100 , F200 , F400 , F500 and below the base plate 103 , 203 , 403 , 503 arranged (see 6a , 6b , 6d , 6e) or the energy transmitting device 320a is over the outer skin AH300 of the aircraft F300 arranged and through the base plate 303 covered (see 6c ).

With the planes F100 , F200 , F300 , F400 , F500 are the controller 107 , 207 , 307 , 407 , 507 and the energy source 110 , 210 , 310 , 410 , 510 in a pressurized cabin DK of the respective aircraft F100 , F200 , F300 , F400 , F500 arranged.

In particular, it is also provided that in the 1 to 4th camera system shown 1 instead of a data transmission line and a power supply line analogous to optionally one of the in the 6a to 6e to equip embodiment variants shown with a wireless data transmission device and a wireless energy transmission alignment.

Furthermore, it is particularly also provided that in the 5 shown aircraft F. alternatively to the camera system 1 or in addition to the camera system 1 which is in the 1 to 4th is described with one or more of the 6a to 6e to equip the camera systems shown.

In the 6a to 6e camera systems shown 101 , 201 , 301 , 401 , 501 is the image sensor element 106 , 206 , 306 , 406 , 506 the camera 105 , 205 , 305 , 405 , 505 in the recording room 112 , 212 , 312 , 412 , 512 of the aerodynamic body 111 , 211 , 311 , 411 , 511 on the adapter 118 , 218 , 318 , 418 , 518 arranged.

In the 7th Figure 3 is a perspective exploded view of another camera system according to the invention 701 shown which as an aircraft camera system 702 is trained. The camera system 701 includes an adapter 718 . The camera system also includes 701 a cover 704 which together with the adapter 718 an aerodynamic body 711 forms, being in the aerodynamic body 711 one versus one environment U closed recording room 712 is trained. The adapter 718 is as a housing 727 executed which an interior 726 includes. In the interior 726 is an image sensor element 706 a camera 705 recorded. The case 727 comprises a housing upper part 727a and a lower housing part 727b , which as a base plate 730 is executed. The housing also includes 727 one with the bottom plate 730 connected stand 731 on which the image sensor element 706 is mounted. The upper part of the housing 727a includes a breakthrough 728 and a disc 729 which made the breakthrough 728 locks. With the base plate 730 is the one as housing 727 trained adapters 718 on a base plate 703 of the camera system 701 attached. This is in turn with a first wing F701 of an airplane F700 connected, with the wing F701 is only indicated schematically. The aerodynamic body 711 and the base plate 703 are designed so symmetrically that the aerodynamic body 711 with the disc 729 can be mounted pointing in the x-direction or that the aerodynamic body 711 without turning the base plate 703 with the disc 729 can be mounted pointing in the x 'direction. Further components of the camera system, not shown 701 are analogous to that in the 1 to 4th execution variant shown or are analogous to one of the in the 6a to 6e Executed execution variants shown.

The one in the 7th camera system shown 701 is the image sensor element 706 the camera 705 in the recording room 712 of the aerodynamic body 711 inside the adapter 718 , namely in the interior 726 of the adapter 18th arranged.

In the 8th Figure 3 is a perspective exploded view of another camera system according to the invention 801 shown in detail. The camera system 801 is as an aircraft camera system 802 educated. A camera 805 of the camera system 801 includes a first adapter 818-1 and a second adapter 818-2 . These are both as a housing 827-1 , 827-2 executed, each having an interior 826-1 , 826-2 include. The camera 805 comprises two image sensor elements 806-1 , 806-2 , wherein the first image sensor element 806-1 in the first interior 826-1 and the second image sensor element 806-2 in the second interior 826-2 is recorded. The two adapters 818-1 , 818-2 form in the assembled state together with a cover 804 an aerodynamic body 811 , with the cover 804 the two adapters 818-1 , 818-2 connects with each other. In the aerodynamic body 811 is an opposite of an environment U closed recording room 812 educated. The adapters 818-1 , 818-2 are identical to the one in the 7th adapter shown. In this respect, the 7th and the associated description. Further components of the camera system, not shown 801 are analogous to that in the 1 to 4th Executed embodiment variant shown or are analogous to one of the in the 6a to 6e Executed execution variants shown.

The one in the 8th camera system shown 801 is the first image sensor element 806-1 the camera 805 in the recording room 812 of the aerodynamic body 811 within the first adapter 818-1 , namely in the interior 826-1 of the first adapter 818-1 arranged and is the second image sensor element 806-2 the camera 805 in the recording room 812 of the aerodynamic body 811 inside the second adapter 818-2 , namely in the interior 826-2 of the second adapter 818-2 arranged.

In the 9 is a perspective exploded view of another camera system according to the invention 901 shown in detail. The camera system 901 is as an aircraft camera system 902 educated. A camera 905 of the camera system 901 includes a first adapter 918-1 , a second adapter 918-2 and a third adapter 918-3 . These are all three as a housing 927-1 , 927-2 , 927-3 executed, each having an interior 926-1 , 926-2 , 926-3 include. The camera 905 includes three image sensor elements 906-1 , 906-2 , 906-3 , wherein the first image sensor element 906-1 in the first interior 926-1 and the second image sensor element 906-2 in the second interior 926-2 and the third image sensor element 906-3 in the third interior 926-3 is recorded. The three adapters 918-1 , 918-2 , 918-3 form in the assembled state together with a cover 904 an aerodynamic body 911 , with the cover 904 the three adapters 918-1 , 918-2 , 918-3 connects with each other. In the aerodynamic body 911 is an opposite of an environment U closed recording room 912 educated. The three adapters 918-1 , 918-2 , 918-3 are identical to the one in the 7th adapter shown. In this respect, the 7th and the associated description. Further components of the camera system, not shown 901 are analogous to that in the 1 to 4th Executed embodiment variant shown or are analogous to one of the in the 6a to 6e Executed execution variants shown.

The one in the 9 camera system shown 901 is the first image sensor element 906-1 the camera 905 in the recording room 912 of the aerodynamic body 911 within the first adapter 918-1 , namely in the interior 926-1 of the first adapter 918-1 arranged and is the second image sensor element 906-2 the camera 905 in the recording room 912 of the aerodynamic body 911 inside the second adapter 918-2 , namely in the interior 926-2 of the second adapter 918-2 arranged and is the third image sensor element 906-3 the camera 905 in the recording room 912 of the aerodynamic body 911 inside the third adapter 918-3 , namely in the interior 926-3 of the third adapter 918-3 arranged.

List of reference symbols

1

Camera system

2

Aircraft camera system

3

Base plate

3a

Top of 3

4th

cover

5

camera

6th

Image sensor element of FIG

7th

Controller of 5

8th

Means of data transmission

9

Means of energy transmission

10

Energy source

11

aerodynamic body

12

Recording room

13

Data transmission line

14th

Power supply line

15th

Opening in 3

16

Sealant for 3

17th

Field of view from 6

18th

Adapter for 6

19th

multipolar coupling agent of 13

19a, 19b

Plug connection from 19

20th

multipolar coupling agent of 14

20a, 20b

Plug connection from 20

21a-21c

screw

22a-22c

thread

23

second image sensor element

24

another sensor

25th

Adapter cable set

26th

Interior from 18

27

Housing from 18

28

Breakthrough from 27

29

Write from 18

92

second camera system at F2

93

third camera system at F3

94

fourth camera system at F4

AH

Outer skin of F

DK

Pressurized cabin from F

F.

plane

F1, F2

first, second wing

F3, F4

first / second end of a tailplane CPR a tail unit LW

CPR

Horizontal stabilizer from F

K21a-K21d

Channel in 4 for 21a , 21b , 21c , 21d

LW

Tail unit from F

P18-1

first position from 18 to 3a from 3

P18-2

second position from 18 to 3a from 3

R.

Hull of F

S3-1, S3-2

Screw to connect 3 and AH

SLW

Vertical stabilizer

U

Surroundings

x

Arrow direction

z

Arrow direction

101, 201, 301, 401, 501

Camera systems

102, 202, 302, 402, 502

Aircraft camera system

103, 203, 303, 403, 503

Base plate

104, 204, 304, 404, 504

cover

105, 205, 305, 405, 505

camera

106, 206, 306, 406, 506

Image sensor element

107, 207, 307, 407, 507

Controller

108, 208, 308, 408, 508

Means of data transmission

109, 209, 309, 409, 509

Means of energy transmission

110, 210, 310, 410, 510

Energy source

111; 211; 311; 411; 511

aerodynamic body

112, 212, 312, 412, 512

Recording room

113, 213, 313, 413, 513

wireless data transmission device

114, 214, 314, 414, 514

wireless energy transmission device

118; 218; 318; 418; 518

adapter

119a, 219a, 319a, 419a, 519a

first data transmitting and receiving device

119b, 219b, 319b, 419b, 519b

second data transmitting and receiving device

120a, 220a, 320a, 420a, 520a

Energy transmitting device

120b, 220b, 320b, 420b, 520b

Energy receiving device.

AH100, AH200, AH300, AH400, AH500

Outer skin

F100, F200, F300, F400, F500

plane

701

Camera system

702

Aircraft camera system

703

Base plate

704

cover

705

camera

706

Image sensor element

711

aerodynamic body

712

Recording room

718

adapter

726

inner space

727

casing

727a

Housing upper part

727b

Housing base

728

breakthrough

729

disc

730

Base plate

731

Stand

F700

plane

F701

first wing of F700

x

direction

x`

direction

801

Camera system

802

Aircraft camera system

804

cover

805

camera

806-1, 806-2

Image sensor element

811

aerodynamic body

812

Recording room

818-1, 818-2

adapter

826-1, 826-2

inner space

827-1, 827-2

casing

901

Camera system

902

Aircraft camera system

904

cover

905

camera

906-1, 906-2, 906-3

Image sensor element

911

aerodynamic body

912

Recording room

918-1, 918-2, 918-3

first adapter

926-1, 926-2, 926-3

inner space

927-1, 927-2, 927-3

casing

QUOTES INCLUDED IN THE DESCRIPTION

This list of the documents listed by the applicant was generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Patent literature cited

• DE 3417917 C2 [0002]

Claims (16)

Camera system (1; 101; 201; 301; 401; 501; 701; 801; 901) for aircraft (F; F100; F200; F300; F400; F500; F700), in particular aircraft camera system (2; 102; 202; 302; 402 ; 502; 702; 802; 902) comprising a cover (4; 104; 204; 304; 404; 504; 704; 804; 904) and a camera (5; 105; 205; 305; 405; 505; 705; 805 ; 905), characterized in that the camera system (1; 101; 201; 301; 401; 501; 701; 801; 901) furthermore comprises a base plate (3; 103; 203; 303; 403; 503; 703), - That the camera (5; 105; 205; 305; 405; 505; 705; 805; 905) physically in an image sensor element (6; 106; 206; 306; 406; 506; 706; 806-1, 806- 2; 906-1, 906-2, 906-3) and a controller (7; 107; 207; 307; 407; 507) is divided, - wherein the camera system (1; 101; 201; 301; 401; 501; 701; 801; 901) means for data transmission (8; 108; 208; 308; 408; 508) by means of which the image sensor element (6; 106; 206; 306; 406; 506; 706; 806-1, 806-2 ; 906-1, 906-2, 906-3) and the controller (7; 107; 207; 307; 407; 507) are connected to transmit the raw data, - the camera system (1; 101; 201; 301; 401; 501; 701; 801; 901) comprising means for energy transmission (9; 109; 209; 309; 409; 509), by means of which the image sensor element (6; 106; 206; 306; 406; 506; 706; 806-1, 806-2; 906-1, 906-2, 906-3) is supplied with electrical energy, - the camera system ( 1; 101; 201; 301; 401; 501; 701; 801; 901) furthermore an adapter (18; 118; 218; 318; 418; 518; 718; 818-1, 818-2; 918-1, 918- 2, 918-3), with which the image sensor element (6; 106; 206; 306; 406; 506; 706; 806-1, 806-2; 906-1, 906-2, 906-3) on the base plate (3; 103; 203; 303; 403; 503; 703) - the cover (4; 104; 204; 304; 404; 504; 704; 804; 904) and the adapter (18; 118; 218 ; 318; 418; 518; 718; 818-1, 818-2; 918-1, 918-2, 918-3) formed in this way and on the base plate (3; 103; 203; 303; 403; 503; 703) are arranged that an aerodynamic body (11; 111; 211; 311; 411; 511; 711; 811; 911) is formed et is which the base plate (3; 103; 203; 303; 403; 503; 703) covered and wherein in the aerodynamic body (11; 111; 211; 311; 411; 511; 711; 811; 911) a receiving space (12; 112; 212; 312; 412; 512; 512; 712; 812; 912), - wherein the image sensor element (6; 106; 206; 306; 406; 506; 706; 806-1, 806-2; 906-1, 906-2, 906-3; 706; 806-1, 806-2; 906-1, 906-2, 906-3) is arranged within the receiving space (12; 112; 212; 312; 412; 512; 712; 812; 912) and wherein the controller (7 ; 107; 207; 307; 407; 507) outside of the receiving space (12; 112; 212; 312; 412; 512; 712; 812; 912) is arranged. Camera system (1; 101; 201; 301; 401; 501; 701; 801; 901) according to Claim 1 , characterized in that the means for data transmission (8; 108; 208; 308; 408; 508) are designed either as a data transmission line (13) or as a wireless data transmission device (113; 213; 313; 413; 513) by means of which the image sensor element (6; 106; 206; 306; 406; 506; 706; 806; 906) is connected to the controller (7; 107; 207; 307; 407; 507) for data transmission and - that the means for energy transmission ( 9; 109; 209; 309; 409; 509) are designed either as an energy supply line (14) or as a wireless energy transmission device (114; 214; 314; 414; 514) by means of which the image sensor element (6; 106; 206; 306 ; 406; 506; 706; 806; 906) is supplied with electrical energy. Camera system (1; 101; 201; 301; 401; 501; 701; 801; 901) according to Claim 2 , characterized in that the base plate (3; 103; 203; 303; 403; 505; 703) comprises an opening (15), the data transmission line (13) and / or the power supply line (14) being guided through this opening (15) and is sealed with respect to the base plate (3; 103; 203; 303; 403; 505; 703) by a sealing means (16). Camera system (1; 101; 201; 301; 401; 501; 701; 801; 901) according to Claim 1 or 2 or 3 , characterized in that the base plate (3; 103; 203; 303; 403; 505; 703) has a spherically curved upper side (3a). Camera system (1; 101; 201; 301; 401; 501; 701; 801; 901) according to at least one of the preceding claims, characterized in that the adapter (18; 718; 818-1, 818-2; 918-1; 918-2; 918-3) is designed as a housing (27; 727; 827-1, 827-2; 927-1, 927-2, 927-3) and that the image sensor element (6; 706; 806-1, 806-2; 906-1, 906-2, 906-3) in an interior (26; 726; 826-1, 826-2; 926-1, 926-2, 926-3) of the housing (27; 727 ; 827-1, 827-2; 927-1, 927-2, 927-3) is added and the housing (27; 727; 827-1, 827-2; 927-1, 927-2, 927-3 ) is attached to an upper side (3a) of the base plate (3; 703), the adapter (18; 718; 818-1, 818-2; 918-1; 918-2; 918-3) optionally in a first position (P18-1) or in at least any further position (P18-2), which deviates from all other positions, on the upper side (3a) of the base plate (3; 703). Camera system (1) according to at least one of the preceding claims, characterized in that the data transmission line (13) and / or the power supply line (14) of the camera system (1) is designed as a multipole line and each has a multipole coupling means (19; 20), the coupling means (19; 20) each comprising a first coupling part (19a; 20a) and a second coupling part (19b; 20b), the coupling parts (19a, 19b; 20a, 20b) in particular as a plug connection or as a rotary -Plug connection are formed. Camera system (1) Claim 6 , characterized in that the first coupling means (19) and / or the second coupling means (20) is arranged in the receiving space (12). Camera system (1; 100; 200; 300; 400; 500) according to at least one of the preceding claims, characterized in that the cover (4; 104; 204; 304; 404; 505; 705; 805; 905) with the base plate ( 3; 103; 203; 303; 403; 503; 703) is screwed. Camera system (801; 901) according to at least one of the preceding claims, characterized in that the camera (805; 905) comprises at least one further image sensor element (806-2; 906-2, 906-3) and that the camera system (801; 901 ) comprises at least one further adapter (818-2; 918-2, 918-3), the further image sensor element (806-2; 906-2, 906-3) on the further adapter (818-2; 918-2, 918-3) is arranged and wherein the further adapter (818-2; 918-2, 918-3) is part of the aerodynamic body (811; 911). Camera system (101; 201; 301; 401; 501) according to at least one of the Claims 2 to 9 - characterized in that - the wireless data transmission device (113, 213; 313; 413; 513) has a first data transmission and reception device (119a, 219a, 319a, 419a, 519a) and a second data transmission and reception device (119b , 219b, 319b, 419b, 519b), - wherein the first data transmitting and receiving device (119a; 219a; 319a; 419a; 519a) is connected to the controller (107, 207, 307, 407, 507) and outside of the The receiving space (112; 212; 312; 412; 512) is arranged either remotely from the base plate (103; 203; 303; 403; 503) or on the base plate (103; 203; 303; 403; 503) and - wherein the second Data transmitting and receiving device (119b, 219b, 319b, 419b, 519b) is connected to the image sensor element (106; 206; 306; 406; 506) and either outside the receiving space (112; 212; 312; 412; 512) below the base plate (103; 203; 303; 403; 503) or in the receiving space (112; 212; 312; 412; 512) on the base plate (103; 203; 303; 403; 503) or on the adapter (11 8th; 218; 318; 418; 518) is arranged. Camera system (101; 201; 301; 401; 501) according to at least one of the Claims 2 to 9 - characterized in - that the wireless energy transmission device (114; 214; 314; 414; 514) has an energy transmission device (120a; 220a; 320a; 420a; 520a) and an energy reception device (120b; 220b; 320b; 420b; 520b ) comprises, - wherein the energy transmission device (120a; 220a; 320a; 420a; 520a) outside of the receiving space (112; 212; 312; 412; 512) either remotely from the base plate (103; 203; 403; 503) or to the base plate (303) and - wherein the energy receiving device (120b; 220b; 320b; 420b; 520b) is connected to the image sensor element (106; 206; 306; 406; 506) and - either in the receiving space (312; 412 ; 512) on the base plate (303; 403; 503) or - in the receiving space on the adapter or - in the receiving space on the image sensor element or - outside the receiving space (112; 212) on the base plate (103; 203). Camera system (101; 201; 301; 401; 501) according to at least one of the preceding claims, characterized in that the camera system (101; 201; 301; 401; 501) at least one further of the image sensor element (106; 206; 306; 406 ; 506) different sensors, the further sensor being arranged in the receiving space (112; 212; 312; 412; 512) and via the means for data transmission (108; 208; 308; 408; 508) and the means for energy transmission ( 109; 209; 309; 409; 509) is preferably connected to the controller (107; 207; 307; 407; 507). Aircraft (F; F100; F200; F300; F400; F500; F700), characterized in that the aircraft (F; F100; F200; F300; F400; F500; F700) has at least one camera system (1; 101; 201; 301; 401; 501; 701; 801; 901) according to at least one of the Claims 1 to 12th includes. Airplane (F; F100; F200; F300; F400; F500; F700) according to Claim 13 , characterized in that the aircraft (F; F100; F200; F300; F400; F500; F700) comprises a pressure cabin (DK) and that the controller (7) of the camera system (1; 101; 201; 301; 401; 501; 701; 801; 901) is arranged within the pressurized cabin (DK) and that the aircraft (F; F100; F200; F300; F400; F500; F700) wing (F1, F2), a tail unit (LW) and a fuselage (R ), the aerodynamic body (11; 111; 211; 311; 411; 511; 711; 811; 911) with its base plate (3; 103; 203; 303; 403; 503; 703) on one of the wings (F1 , F2) or on the tail unit (LW) or on the fuselage (R). Airplane (F100; F200; F300; F400; F500) according to Claim 13 or 14th , characterized in - that the first data transmitting and receiving device (119a, 219a, 419a, 519a) under a Outer skin (AH100; AH200; AH400; AH500) of the aircraft (F100; F200; F400; F500) and below the base plate (103; 203; 403; 503) is arranged or - that the first data transmission and reception device (319a) is arranged over an outer skin (AH300) of the aircraft (F300) and is covered by the base plate (303). Airplane (F100; F200; F300; F400; F500) according to Claim 13 or 14th or 15th , characterized in that - that the energy transmission device (120a, 220a, 420a, 520a) under an outer skin (AH100; AH200; AH400; AH500) of the aircraft (F100; F200; F400; F500) and under the base plate (103; 203 ; 403; 503) or that the energy transmission device (320a) is arranged over an outer skin (AH300) of the aircraft (F300) and is covered by the base plate (303).

Images