The invention relates to an aircraft with modular structure.
In aircraft, especially for civil aviation, there are particularly stringent requirements relating to the flexibility of equipment- and performance characteristics.
It is the object of the invention to create an aircraft that can be flexibly adapted to different equipment- and performance characteristics.
This object is met as disclosed in claim 1. Advantageous embodiments of the invention are stated in the dependent claims.
According to an exemplary embodiment of the invention an aircraft comprises a module carrier for accommodating a plurality of module elements in which in each case at least one system element is integrated. The system elements assume individual tasks that are necessary in relation to the aircraft or the flight mission. In this arrangement it is also possible for several system elements to be present within one module element.
By changing individual or all modules, in this way it is possible to achieve different equipment- and performance variants of the same aircraft model. Furthermore, by leaving out individual module elements that are not required at the time for a particular mission, it becomes possible to activate savings potentials by means of a reduction in weight.
In each case the module elements and/or the system elements are networked among each other. By networking system elements also among different module elements, the capability of the overall system can be influenced or adapted. Furthermore, with this design the balance of the aircraft can be influenced.
According to another exemplary embodiment of the invention, it is possible to design passenger module elements that are boarded by passengers, or to design freight module elements that are filled with freight, while these module elements are outside the aircraft, with said module elements subsequently being placed in a corresponding accommodation device of the aircraft. Furthermore, it is possible for these passenger modules or freight modules to be moved (transported) also by other means of transport, for example by rail, ship, etc.
Below, with reference to
As shown in
According to the exemplary embodiment, the aerofoil 10 comprises an external system module 11, for example an auxiliary tank. Although not shown in the figure, a plurality of such external modules can be affixed to the outside of the aerofoil 10 or the fuselage of the aircraft 1.
According to the exemplary embodiment, the fuselage of the aircraft 1 comprises two freight modules 7 in order to accommodate freight (not shown). Above the freight modules 7 in each case there are floor modules 8. According to the exemplary embodiment, above the floor modules 8 there are passenger modules 5, 6 for accommodating passengers.
Furthermore, according to the exemplary embodiment, the aircraft 1 comprises propulsion modules 4 to generate movement of the aircraft 1 and thus a flow against the aerofoil 10, which flow is necessary to generate lift.
According to the exemplary embodiment, the aircraft 1 further comprises two tank modules 9, which are arranged in the fuselage of the aircraft 1.
As shown in
In each instance the above-mentioned module elements comprise integrated system elements that are networked among each other. Furthermore, the individual module elements or their integrated system elements are networked with each other so as to meet a required equipment- and performance characteristic of the aircraft 1.
Although the invention was described with reference to an exemplary embodiment, it is of course possible to make modifications and changes without leaving the protective scope of the invention.
For example, other module elements, either more or fewer of them, can be used, depending on the respective requirements relating to the aircraft 1 or to the aircraft mission.
Furthermore, the system elements integrated in the individual module elements can be any imaginable system elements, for example comprising: a hydraulic system element; a pneumatic system element; an energy supply system element; an electrical system element; a cooling system element; an air conditioning system element; a water supply system element; a waste water disposal system element; a gas supply system element; a liquid supply system element; an exhaust gas disposal system element; a liquid disposal system element; a communication system element; a control system element; a data transmission system element; an emission element for heat or light; an element for functions of the aircraft operation; an element for safety functions; an element for comfort or the supply to passengers or crew; an element for the transport of passengers, for example a seating cabin or a sleeping cabin; an element for the transport of freight, etc.
Any number and any type and manner of the above-mentioned individual system elements can be integrated in the individual above-mentioned module elements.
1 Aircraft
2 Module carrier
3 Module element
4 Propulsion module element
5 Passenger module element
6 Passenger module element
7 Freight module element
8 Floor module element
9 Tank module element
10 Aerofoil/Wing
11 External module element
12 Supply-/disposal module element
Number | Date | Country | Kind |
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10 2005 060 369.6 | Dec 2005 | DE | national |
This application claims the benefit of the filing date of German Patent Application No. 10 2005 060 369.6 filed Dec. 16, 2005 and of U.S. Provisional Application 60/750,955 filed Dec. 16, 2005, the disclosure of which applications is hereby incorporated herein by reference.
Filing Document | Filing Date | Country | Kind | 371c Date |
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PCT/EP2006/012142 | 12/15/2006 | WO | 00 | 9/18/2009 |
Number | Date | Country | |
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60750955 | Dec 2005 | US |