STIRLING ENGINE FOR AN EMISSION-FREE AIRCRAFT

Abstract

Aircraft with an emission-free drive and method for emission-free driving of an aircraft. The aircraft includes an aircraft thruster structured and arranged to generate thrust force on the aircraft, an aircraft lift device structured and arranged to generate lift on the aircraft, and a heat engine, which is structured and arranged to convert thermal energy into kinetic energy to drive the aircraft thruster, that includes at least one flat-plate Stirling engine drivable by solar thermal radiation.

Claims

1. An aircraft with an emission-free drive, comprising: an aircraft thruster structured and arranged to generate thrust force on the aircraft; an aircraft lift device structured and arranged to generate lift on the aircraft; and a heat engine, which is structured and arranged to convert thermal energy into kinetic energy to drive the aircraft thruster, comprising at least one flat-plate Stirling engine drivable by solar thermal radiation.

2. The aircraft according to claim 1, wherein the aircraft lift device comprises a wing with an airfoil section structured and arranged to generate lift, and the flat-plate Stirling engine is arranged in the wing.

3. The aircraft according to claim 1, the flat-plate Stirling engine comprising: a working chamber filled with a working gas and having a top and an underside and a changeable working volume; a displacer structured and arranged to be moveable in the working chamber between the top and the underside; a regenerator structured and arranged in the working chamber to collect and deliver thermal energy contained in the working gas; a working piston connected to change a working volume of the working chamber; a rotatable inertia element comprising at least one of a propeller or a flywheel; a drive structured and arranged to be connectable to the inertia element to drive the aircraft thruster; and a transmission structured and arranged to mechanically couple the displacer and the working piston with the inertia element, wherein the working chamber is located in the aircraft lift device and the working gas is heatable from a top of the aircraft lift device by the solar thermal radiation.

4. The aircraft according to claim 3, further comprising a light-transmitting cover arranged in the aircraft lift device in the top region of the working chamber.

5. The aircraft according to claim 1, further comprising a power-generator structured and arranged to generate electric energy to drive the aircraft.

6. The aircraft according to claim 5, the power-generator comprising a generator structured and arranged to convert kinetic energy into electric energy and to be driven by the flat-plate Stirling engine.

7. The aircraft according to claim 5, the power-generator comprising photovoltaic elements for converting solar radiation into electric energy.

8. The aircraft according to claim 5, the power-generator comprising a fuel cell device, wherein the fuel cell in operation releases heat that is fed to a working chamber of the flat-plate Stirling engine.

9. The aircraft according to claim 5, further comprising an electric storage structured and arranged to store and deliver the electric energy generated by the power-generator, wherein the power-generator is arranged to feed the electric energy to the electric storage and the electric storage is structured and arranged to store the electric energy and to make the stored electric energy available for driving the aircraft.

10. A method for emission-free driving of an aircraft, comprising: receiving solar thermal energy by a flat-plate Stirling engine; converting the thermal energy into kinetic energy via the flat-plate Stirling engine; and driving, via the flat-plate Stirling engine, an aircraft thruster.

11. The method according to claim 10, wherein: in a first phase, converting kinetic energy of the flat-plate Stirling engine into electric energy and storing the electric energy; and in a second phase, converting the stored electric energy into thermal energy in an electric heater, and driving the Stirling engine to provide the kinetic energy for driving the aircraft thruster.

12. The aircraft according to claim 1, wherein the aircraft lift device comprises a wing shaped body or a fluid filled body.

13. The aircraft according to claim 1, wherein the aircraft comprises an airplane or an airship.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0101] The present invention is further described in the detailed description which follows, in reference to the noted plurality of drawings by way of non-limiting examples of exemplary embodiments of the present invention, in which like reference numerals represent similar parts throughout the several views of the drawings, and wherein:

[0102] FIG. 1 illustrates an aircraft with an emission-free drive according to an exemplary embodiment of the invention,

[0103] FIG. 2 illustrates a further exemplary embodiment of an aircraft according to the invention;

[0104] FIG. 3 illustrates a diagrammatic section through a wing device of an aircraft according to an exemplary embodiment of the invention;

[0105] FIG. 4 illustrates a further exemplary embodiment of an aircraft according to the invention;

[0106] FIG. 5 illustrates a vertical section through a further exemplary embodiment of a wing device according to the invention;

[0107] FIG. 6 illustrates a further exemplary embodiment of an aircraft according to the invention;

[0108] FIG. 7 illustrates a vertical section through a further exemplary embodiment of a wing device according to the invention;

[0109] FIG. 8 illustrates a vertical section through a further exemplary embodiment of a wing device according to the invention;

[0110] FIG. 9 illustrates a further exemplary embodiment of a wing device in vertical section with a heating device according to the invention;

[0111] FIG. 10 illustrates a further exemplary embodiment of a wing device in vertical section with a further example of a heating device according to the invention;

[0112] FIG. 11 illustrates a further exemplary embodiment of a wing device according to the invention in vertical section;

[0113] FIG. 12 illustrates a further exemplary embodiment of a wing device in vertical section according to the invention with a storage device for storing and delivering electric energy;

[0114] FIG. 13 illustrates process steps of a method according to the invention for driving an aircraft according to an exemplary embodiment of the invention;

[0115] FIG. 14 illustrates a further example of a method according to the invention; and

[0116] FIG. 15 illustrates a displacer with an integrally formed heating device.

DETAILED DESCRIPTION OF THE EMBODIMENTS

[0117] The particulars shown herein are by way of example and for purposes of illustrative discussion of the embodiments of the present invention only and are presented in the cause of providing what is believed to be the most useful and readily understood description of the principles and conceptual aspects of the present invention. In this regard, no attempt is made to show structural details of the present invention in more detail than is necessary for the fundamental understanding of the present invention, the description taken with the drawings making apparent to those skilled in the art how the several forms of the present invention may be embodied or formed in practice.

[0118] FIG. 1 shows a first example of an aircraft 10 with an emission-free drive 12, which is explained in more detail in the following figures. The aircraft 10 has a drive device 14 for generating a thrust, for example in the form of two propeller devices 16, 18. Moreover the aircraft 10 has a lift device 20 for generating a lift, for example, in the form of two lateral wings 22, 24.

[0119] Furthermore, a heat engine 26, not shown in detail, is provided for converting thermal energy into kinetic energy for driving the drive device. To this end, according to the present embodiments of the invention, at least one flat-plate Stirling engine 28 is provided as a motor, which can be driven by solar thermal radiation (not shown in FIG. 1).

[0120] The aircraft is, for example, an airplane, particularly manned and unmanned airplanes can be provided. Moreover, in addition to an airplane, embodiments of the invention include airships, which are, however, not shown in detail.

[0121] FIG. 1 shows by way of example an aircraft 10, e.g., a manned aircraft, that has diagrammatically an airplane tip 30 and a tail region 32. A tailplane 34 and an elevator unit 36 are indicated in the tail region 32. A dashed line 38 designates a longitudinal axis of the airplane, and a direction arrow 40 shows the flight direction.

[0122] FIG. 2 shows a further exemplary embodiment in which, instead of the two propeller devices 16, 18, a propeller device 41 provided in the region of the airplane tip 30 is shown.

[0123] Naturally, a larger number of propeller devices can also be provided. For example, the propeller device 41 can be combined with the two propeller devices 16, 18 or with two or more propeller devices along the wings. Moreover, more than two propellers 16, 18 can be arranged along the wings without propeller 41.

[0124] The flat-plate Stirling engine 28 can be embodied or formed, for example, in an upper region of the fuselage construction, as is shown with a dashed line 43 in FIG. 2, in order to drive via a connection 42, the center propeller of the propeller device 41.

[0125] Alternatively or additionally, in FIG. 1 it is indicated by a dashed line 44 that the flat-plate Stirling engine 28 is integrated into the lift device 20. In other words, the lift device 20, which comprises a wing device 46 with an airfoil section 48 for generating a lift, serves to accommodate the at least one flat-plate Stirling engine 28.

[0126] The flat-plate Stirling engine 28 is explained in more detail with reference to FIG. 3, in which the flat-plate Stirling engine 28 is shown accommodated in the wing device 46. However, it is understood that the flat-plate Stirling engine 28 can also be provided at other locations, such as, e.g., in the upper fuselage region or also in the front region of the airplane.

[0127] The flat-plate Stirling engine 28 has a working chamber 52 filled with a working gas 50, and includes a top 54 and an underside 56 and a changeable working volume 58. Moreover, a displacer 60 is held in the working chamber 52 in a moveable manner between the top 54 and the underside 56. Furthermore, a regenerator 62 is arranged in the working chamber 52 for collecting and delivering thermal energy contained in the working gas 50. Furthermore, a working piston 64 is connected to the working chamber 52. The working piston 64 is used to change the working volume 58. Furthermore, an inertia element 66 is held in a rotatable manner, and an output 68 is connected to the inertia element 66 for driving the drive device, for example, the propeller 16 or 18 and/or 41. Moreover, a transmission device 70 mechanically couples the displacer 60 and the working piston 64 to the inertia element 66. The working chamber 52 is arranged in the lift device and the working gas 50 can be heated by solar thermal radiation, indicated symbolically by arrows 74, from a top 72 of the lift device.

[0128] The transmission device 70 has a first push rod connection 75 which couples the displacer 60 at a first pivot point 76 of the inertia element 66. Moreover, the transmission device 70 has a second push rod connection 78, which couples the working piston 64 at a second pivot point 80 of the inertia element 66. The first pivot point 76 on the inertia element 66 is arranged offset by 90 in its rotation angle position in a rotation direction 82 in front of the second pivot point 76.

[0129] The working piston 64 is held in a moveable manner in a working cavity 84 and forms a moveable wall surface of the working chamber 52.

[0130] As indicated diagrammatically in FIG. 3, the working chamber 52 is embodied or formed between a top of a wing 86 and an underside of a wing 88. The displacer 60 divides the working chamber 52 into a first, i.e., upper chamber region and a second, i.e., lower chamber region. The displacer 60 is thereby embodied or formed so that with movement about a pivot point 90, working gas 50 is displaced from the one chamber region into the other chamber region. The top of the wing 86 thereby forms a first side of the flat-plate Stirling engine 28 with a first temperature, and the underside of the wing 88 forms a second side of the flat-plate Stirling engine 28 with a second temperature. The second temperature is lower than the first temperature.

[0131] For example, an aluminum sheet can be provided on the underside 88 for cooling.

[0132] With movement of the displacer 60, working gas 50 flows through the regenerator 62, which is sealed to the front region of the wing cavity by a bulkhead 92. The bulkhead 92 forms a wall running between the top of the wing and the underside of the wing which closes the working chamber 52 with respect to the front region.

[0133] The flat-plate Stirling engine 28 can be embodied or formed, for example, between adjacent rib constructions of the wing, and the bulkhead 92 can be embodied or formed in connection with an airfoil section running in the longitudinal direction. The flat-plate Stirling engine 28 can be used, for example, for wing statics or be integrated into the support structure concept. According to embodiments, several flat-plate Stirling engines can also be embodied or formed in the longitudinal direction of the wing, which runs transversely to the actual flight direction, i.e., the longitudinal axis 38 of the airplane.

[0134] The displacer 60 can in particular be embodied or formed as a plate bent in the direction of the airfoil profile, in order to be able to optimally utilize the wing geometry.

[0135] The displacer 60 can be formed from or include, for example, a fiberboard with at least one thermal insulation property, having top a dark color on a top surface, e.g., a foam board painted black. A sufficiently stable board material can be provided, which also includes only a very low weight. The provision of a dark color on the top supports the heating up of the working gas 50 in the upper region, i.e., the upper chamber.

[0136] To this end, for example, the lift device in the region of the working chamber 52 on the top can have a light-transmitting cover 94. The light-transmitting cover 94 can be embodied or formed thereby, for example, in a transparent or also translucent manner, the important factor is that sufficient thermal radiation can enter the region of the working chamber 52. For example, shortwave solar radiation can enter the region in order to be converted there into longwave thermal radiation.

[0137] The cover or exterior skin of the wing device can thereby also at the same time form the chamber wall in the region of the working chamber 52.

[0138] As shown in FIG. 4, a further exemplary embodiment is directed to a power-generating device 96 that is diagrammatically illustrated in FIG. 4, and can be provided for generating electric energy for driving the aircraft.

[0139] For example, as shown in FIG. 5, the power-generating device 96 can comprise a generator device 98 for converting kinetic energy into electric energy. The generator device 98 is driven by the flat-plate Stirling engine 28.

[0140] At this point it should be noted that the connection of the inertia element 66 to the drive device, i.e., the propeller, as well as the connection to the generator device 98 are shown merely diagrammatically as a type of bevel gear connection. Of course, other transmission connection mechanisms can also be used here.

[0141] According to a further exemplary embodiment, the power-generating device 96 can have photovoltaic elements 100 for converting solar radiation into electric energy. FIG. 6 shows, for example, that the photovoltaic elements 100 can be arranged in the region of the roof construction 102 or in the region of the front airplane tip 104 and/or also in the region of the wings 106.

[0142] According to a further exemplary embodiment, which is shown in FIG. 7, the photovoltaic elements are arranged on the top of the displacer, which is indicated by a double line 108.

[0143] The power-generating device 96 according to a further exemplary embodiment can also have a fuel cell device 110, for example, accommodated inside the fuselage construction, as is indicated diagrammatically in FIG. 4. The fuel cell device 110 can also be arranged inside a wing construction, as is shown in FIG. 8. It can thereby also be provided, for example, that the heat released with a fuel cell operation is fed to the working chamber of the flat-plate Stirling engine (not shown in further detail in FIG. 8).

[0144] According to a further exemplary embodiment, a heating device 112 for heating the working gas is provided in one of the two chamber regions of the working chamber of the flat-plate Stirling engine, i.e., in the hotter region of the working chamber.

[0145] For example, the heating device 112 can have an electric heating device 114 for converting electric energy into thermal energy. The electric heating device 114 is attached to the displacer 60, as is shown in FIG. 9, or the electric heating device 114 is embodied or formed, for example, integrally in the displacer 60, as is shown by the dashed lines in FIG. 15. The heating device 114 can be a heating coil, for example, as is indicated in FIG. 9 or as a resistance layer, not shown in detail, on the displacer 60, which produces heat inside the working chamber by electric energy.

[0146] According to a further exemplary embodiment of the invention, which is shown in FIG. 10, the heating device can have a combustion device 116 operated with a fuel. Additionally, a storage device 118 is provided to store the fuel. The combustion device 116 can be provided in the immediate vicinity of the flat-plate Stirling engine 28, as is indicated in FIG. 10, or at a different location, however, for example, inside the fuselage construction, in order to transport the heat from there to the flat-plate Stirling engine 28 (not shown in detail).

[0147] According to the exemplary embodiment shown in FIG. 11, an electric motor 120 connected to the drive device, for example, the propeller device 16, 18 and/or 41 and can be operated with electric energy of the power-generating device (not shown in detail in FIG. 11).

[0148] FIG. 12 shows a further exemplary embodiment in which a storage device 122 for storing and delivering the electric energy generated by the power-generating device 96 is provided. The power-generating device 96 feeds electric energy to the storage device 122 and the storage device 122 stores the fed electric energy and provides this for operating the aircraft.

[0149] FIG. 12 shows that the storage device 122, for example, is provided as a battery pack which can be accommodated at different locations inside the wing or also inside the fuselage construction (not shown in detail), as is indicated merely by way of example for a first position 124 and a second position 126.

[0150] The storage device 122, for example, delivers the electric energy to the electric heating device 114. The storage and the delivery of the electric energy by the storage device can thereby take place at different phases.

[0151] The storage device 122 can also however, additionally or alternatively, deliver the electric energy to an electric motor, for example, the electric motor 120, which is connected to the drive device.

[0152] According to an embodiment variant of the aircraft, the flat-plate Stirling engine 28 is embodied or formed with the photovoltaic elements 100, with which the electric motor 120 can be operated to support the flat-plate Stirling engine 28. It should be noted that this embodiment variant as well as the embodiment variants shown below are not represented, but the described combinations are understandable for the person skilled in the art from the above described representations of the individual components.

[0153] According to a further embodiment variant, the flat-plate Stirling engine 28 is combined with the photovoltaic elements 100 that deliver the electric current, which can be generated by the solar insulation during the day, to the battery and/or several batteries, i.e., the electric storage device 122, in order to generate a thrust with the electric motor 120 for times when solar thermal radiation is not available to the flat-plate Stirling engine 28.

[0154] According to a further embodiment variant, the flat-plate Stirling engine 28 is combined with the generator device 98, in order to conduct current to the storage device 122 during the day, in order subsequently to be able to operate the aircraft even in the dark by the electric motor 120. The generator 98 can be embodied or formed integrated with the electric motor 120, i.e., to put it simply, the electric motor 120 can also be used in the reverse direction as a generator.

[0155] According to a further embodiment variant, the flat-plate Stirling engine 28 is combined with the photovoltaic elements 100, and with the battery or the storage device 122. Moreover, the electric heating device 114 is provided, in order thus, for example, to feed thermal energy at night to the flat-plate Stirling engine 28, in order to be able to operate the drive device 14 with the flat-plate Stirling engine 28.

[0156] According to a further embodiment variant, the flat-plate Stirling engine 28 is combined with the generator or the generator device 98 and the storage device 122. The stored current can then be fed at night to the electric heating device 114 in order to operate the drive device 14. The embodiment of the generator is thereby in particular advantageous, which can be embodied or formed to be much smaller and lighter compared to an electric motor for driving the drive device.

[0157] According to a further embodiment variant, the flat-plate Stirling engine 28 is combined with the heating device or the combustion device 116, by which thermal energy can be generated during nighttime hours, and is fed to the flat-plate Stirling engine 28 in order to operate the drive device 14 therewith.

[0158] According to a further embodiment variant, the flat-plate Stirling engine 28 is combined with the photovoltaic elements 100, which operate the electric heating device 114 during the day in order to make additional heat available to the flat-plate Stirling engine 28 in addition to the solar thermal radiation. Due to the combination with the photovoltaic elements, the surface of the airplane, which is exposed to the solar insulation, or the thermal radiation can be used optimally and not only those regions that are arranged immediately above the flat-plate Stirling engine working chamber.

[0159] Of course, the embodiment variants described above can also be combined with one another in order to thus to make available overall the best possible utilization of the drive concept of the flat-plate Stirling engine 28.

[0160] Finally FIG. 13 shows a further exemplary embodiment of a method 200 for driving an aircraft, which comprises the following steps: in a first step 210, solar thermal energy is fed to a flat-plate Stirling engine which is provided in the aircraft as a heat engine, in order to drive a drive device to generate a thrust. In a second step 212, the thermal energy is converted by the flat-plate Stirling engine into kinetic energy. In a third step 214, a driving of the drive device by the flat-plate Stirling engine takes place.

[0161] The first step 210 is also referred to as step a), the second step 212 as step b) and the third step 214 as step c). The steps a), b) and c) naturally take place at the same time in a continuous manner during the operation of the aircraft.

[0162] According to a further exemplary embodiment, which is shown in FIG. 14, in a first phase, kinetic energy of the flat-plate Stirling engine is converted into electric energy in a conversion operation 216 and is stored as electric energy. In a second phase, the stored electric energy is converted into thermal energy in a second conversion step 218 and thereby drives the Stirling engine in order to make available the kinetic energy for driving the driving device.

[0163] The first phase is also referred to as step i) and the second phase as step ii). The first phase is provided, for example, with existing solar thermal radiation and the second phase with reduced or unavailable solar thermal radiation, for example at night. The storage and delivery of the electric energy by the storage device thus takes place at different phases, for example, which is why the connection arrows of the first conversion step 216 and the second conversion step 218 are shown by dashed lines in each case.

[0164] According to a further exemplary embodiment, but not shown in detail, it is provided with the method that the kinetic energy is converted into electric energy by the generator mentioned above. Additionally or alternatively, the electric energy can also be made available, for example, by photovoltaic elements or also by a fuel cell, as was explained above based on the different device variants, which is why an explicit representation of corresponding method diagrams is omitted.

[0165] According to a further aspect of the invention, due to the combination of the flat-plate Stirling engine with an additional generation of electric energy during the day and the delivery of the electric energy and subsequent conversion into thermal energy at night, an airplane is possible that flies permanently or in an unlimited manner, which derives its drive from solar heat. In addition to the solar insulation during the day for the Stirling engine, at night as it were an alternative energy source is provided, which can be stored during the day to be available at night. To this end the heat is converted into movement from the heat engine in the form of the Stirling engine and the movement is converted into current by a generator. A battery can therefore store the excess energy during the day in order to convert it at night into heat again and to thereby drive the heat engine in the form of the flat-plate Stirling engine. In particular, the high efficiency of the flat-plate Stirling engine with the utilization of the thermal energy and the high yield of the electric energy with the generation of thermal energy is to be noted, which overall ensures high efficiency.

[0166] The exemplary embodiments described above can be combined in different ways.

[0167] In addition it should be noted that comprising does not exclude any other elements or steps and one does not exclude a plural. Furthermore, it should be noted that features or steps that have been described with reference to one of the above exemplary embodiments can also be used in combination with other features or steps of other exemplary embodiments described above.

[0168] It is noted that the foregoing examples have been provided merely for the purpose of explanation and are in no way to be construed as limiting of the present invention. While the present invention has been described with reference to an exemplary embodiment, it is understood that the words which have been used herein are words of description and illustration, rather than words of limitation. Changes may be made, within the purview of the appended claims, as presently stated and as amended, without departing from the scope and spirit of the present invention in its aspects. Although the present invention has been described herein with reference to particular means, materials and embodiments, the present invention is not intended to be limited to the particulars disclosed herein; rather, the present invention extends to all functionally equivalent structures, methods and uses, such as are within the scope of the appended claims.