Flying object capable of vertical takeoff and landing

Abstract

The invention relates to a flying object (1) capable of vertical takeoff and landing, comprising a fuselage (2) with a longitudinal axis (L) and a plurality of covers (30) arranged on the fuselage (2), wherein at least one of the covers (30) is rotatably mounted about a transverse axis (Q) arranged at an angle to the longitudinal axis (L), and wherein the flying object (1) comprises at least one drive unit (10) having a rotatable turbine (20) and one of the covers (30), wherein the rotatable turbine (20) has an axis of rotation (R) rotatable about the transverse axis (Q), and the cover (30) has a substantially cylindrical section (31) extending along the axis of rotation (R), wherein the cylindrical section (31) coaxially surrounds the turbine (20). The cover (30) is designed to generate lift, in particular in horizontal flight of the flying object (1), wherein the cover is thus designed as an annular wing.

Description

Technical Field

[0001] The invention relates to a flying object that can take off and land vertically, comprising a fuselage with a longitudinal axis and a plurality of covers arranged on the fuselage, wherein at least one of the covers is supported rotatably about a transverse axis arranged at an angle to the longitudinal axis, and wherein the flying object comprises at least one drive device having a rotatable turbine and one of the covers, wherein the rotatable turbine has an axis of rotation that can be rotated about the transverse axis, and the cover has a substantially cylindrical section extending along the axis of rotation, wherein the cylindrical section coaxially surrounds the turbine. Background Art

[0002] US Pat. No. 7,472,863 B2 discloses a flying object of this type capable of vertical takeoff and landing, in which each cover is part of a lift device, thereby enabling the flying object to uniformly generate lift and propulsion using a drive device arranged on the fuselage. The flying object also has two wings that generate lift during essentially horizontal cruising flight. However, in vertical flight (i.e., in ascending and / or descending flight) or in flight with a vertical motion component, the wings create flow resistance that hinders vertical movement. Furthermore, the design and manufacture of the wings are complex. In horizontal flight, the covers of the drive devices create significant and unavoidable flow resistance that reduces the energy efficiency of the flying object. In horizontal flight, the wings are located on the leeward side of the covers, which reduces their effectiveness. Summary of the Invention

[0003] The present invention is based on the object of providing a flying object which has improved aerodynamics independently of the flight mode and which allows for a simpler construction.

[0004] According to the present invention, the cover is designed as an annular wing, that is, in the form of a partially cylindrical, for example, airfoil with a main body open on both sides through which air can flow. The annular wing can generate lift by allowing air to flow around it. The present invention recognizes that the cover, due to its annular wing shape, can serve not only as a lifting body but also, together with a turbine, as a drive body. This improves the aerodynamics of the flying object, particularly when the flying object moves in the direction of the axis of rotation, wherein the axis of rotation is also the direction of the propulsion force achieved by the drive.

[0005] Since the cover is designed as an annular wing, additional wings on the aircraft fuselage become superfluous, thereby simplifying the structure and design of the aircraft. Furthermore, this can save weight. The annular wing-shaped cover replaces conventional wings according to the prior art or can supplement such conventional wings on the aircraft. In particular, several and / or all of the covers can be designed as annular wings.

[0006] The drive and thus the rotatability of the annular wing-shaped cover ensure that the flow resistance is improved independently of the flight mode, ie both during take-off and / or descent and during cruising flight.

[0007] The annular wing shape of the cover improves aerodynamics, avoids energetically disadvantageous turbulence in the airflow generated by the movement, and reduces the flow resistance induced by the airflow. In particular, the cruising characteristics of the aircraft are improved, which increases its range, stability, and safety, and improves cruising speed. The cylindrical section of the drive cover coaxially surrounding the turbine creates an encapsulated drive, which reduces the noise level generated by the turbine and protects the turbine.

[0008] In a preferred embodiment, the cover is rotatable through at least 80° and / or 360° about a transverse axis. The rotatability of the cover and / or the drive unit through at least 80° allows the cover to be oriented vertically, in particular with the axis of rotation, for example, for ascending and / or descending flight, and to be oriented substantially horizontally, in particular with the axis of rotation, for cruising flight that proceeds substantially in a horizontal direction. For cruising flight, the axis of rotation can also be adjusted so that the drive unit and / or the turbine generate propulsion in a direction with a vertical component. This ensures that the induced drag of the cover is minimized, independent of the flight direction and flight mode. It is also possible for the cover and / or the drive unit to be rotatable through at least 90° for this purpose. The 360° rotatability of the cover and / or the drive unit allows for free orientation of the cover and / or the drive unit, for example, so that the aircraft can be braked during cruising flight and / or accelerated during descent flight.

[0009] Advantageously, the plurality of covers are arranged around the fuselage in such a way that at least one cover is arranged at a different position in the direction of the longitudinal axis than another cover and / or at least one cover is arranged at a different position transversely to the longitudinal axis than another cover. If at least two covers and / or the drive devices are arranged at different positions in the direction of the longitudinal axis, this improves the stability and / or controllability of the aircraft with respect to the tilting of the aircraft about an axis transverse to the longitudinal axis. As a result, the aircraft can be stabilized with respect to pitch. If at least two covers and / or the drive devices are arranged at different positions transversely to the longitudinal axis, this improves the stability and / or controllability of the aircraft with respect to the tilting of the aircraft about an axis parallel to the longitudinal axis. As a result, the aircraft can be stabilized with respect to roll.

[0010] The flying object preferably has at least two drive units, and at least two turbines are arranged to rotate in opposite directions to compensate for gyroscopic forces. In particular, the two turbines arranged to rotate in opposite directions can be arranged at two different positions transverse to the longitudinal axis to prevent the flying object from tumbling, i.e., movement of the flying object about the longitudinal axis. For example, the two turbines can have propellers with different directions of rotation.

[0011] Advantageously, the flying object has at least three, preferably four, covers in order to provide a flying object that can be controlled and driven particularly simply and efficiently.

[0012] In a preferred embodiment of the present invention, the flying object has an annular wing-shaped cover that is rotatable about a transverse axis extending transversely to the longitudinal axis. The cover has no turbine arranged therein, as the cover generates lift solely through its annular wing shape and can thus contribute to the control and / or stabilization of the flying object. In particular, the flying object can have multiple covers without turbines.

[0013] The present invention also solves the problem on which the invention is based by providing a cover for an aircraft capable of vertical takeoff and landing, wherein the cover has a substantially cylindrical section, wherein a turbine having an axis of rotation can be coaxially arranged in the cylindrical section. Due to the cylindrical section, the cover of the turbine also does not have its own longitudinal axis, along which the cylindrical section extends, and which, for simplicity, is referred to below as the axis of rotation.

[0014] According to the invention, the cover is designed as an annular wing to improve the aerodynamics of the cover. The cover according to the invention can thus be used as a lift mechanism. Optionally, the cover can form a drive device together with a turbine coaxially arranged in the cylindrical section.

[0015] According to the present invention, the cover has a receiving mechanism that is designed to rotatably mount the cover on the fuselage of an aircraft about a transverse axis. This allows the cover to be used for aircraft capable of vertical takeoff and landing, wherein rotation of the cover about the transverse axis advantageously allows the cover to be oriented for different flight modes, particularly vertically for ascending and / or descending flight, or horizontally for cruising flight. In particular, the cover can be mounted, for example, on a shaft that is rotatably mounted about the transverse axis.

[0016] In a preferred embodiment of the present invention, the hood has a cross-section that tapers along the axis of rotation to improve the hood's aerodynamics. The hood's cross-section can, in particular, taper against the direction of flight, starting from a cylindrical section, particularly arranged in the direction of flight, to such an extent that undesirable flow separation can be prevented and / or turbulence generated at the hood can be minimized. Preferably, the hood has inclined and / or curved end faces to further improve the hood's aerodynamics. To this end, the end faces of the hood can have at least one recess and / or at least one flow deflector projecting along the axis of rotation. The hood can, in particular, have two flow deflectors that project forward at an angle of 60° to 130°, preferably 75° to 120°, and particularly preferably 115°, relative to each other. This leads to further improved aerodynamics and reduced flow resistance, and can also result in further improved lift for the hood. The flow deflectors ensure that turbulent wakes are only generated in the region of the flow deflectors when air flows around the hood, further improving aerodynamics. Flow deflectors can increase lift in particular during cruising flight.

[0017] In another preferred embodiment of the present invention, the outer side of the cover has a first section extending parallel to the axis of rotation and a second section extending parallel to the axis of rotation, wherein the first section has a greater curvature than the second section. This results in the cover being asymmetrical in cross-section transversely to the axis of rotation, which, in particular in horizontal flight, i.e., when the flying object is moving substantially horizontally and the axis of rotation is oriented substantially horizontally, leads to lift generated by the flow around the cover. Advantageously, the first section is arranged diametrically opposite the second section to utilize the lift generated by the flow around the cover as efficiently as possible.

[0018] The described flying objects can be combined in all embodiments with all advantageous embodiments of the enclosure.

[0019] Further preferred embodiments of the invention result from the features mentioned in the remaining dependent claims.

[0020] The different embodiments of the invention mentioned in this application can advantageously be combined with one another, unless they are implemented otherwise in each case. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The present invention will be explained below in the following examples with reference to the accompanying drawings, wherein:

[0022] Figure 1 A perspective view showing a flying object according to an embodiment of the present invention;

[0023] Figure 2 Show Figure 1 A side view of the flying object shown in;

[0024] Figure 3 Show Figure 1 and Figure 2 A top view of the flying object shown in ;

[0025] Figure 4 shows a longitudinal section of the drive unit;

[0026] Figure 5 Showing a side view of the cover;

[0027] Figure 6 Show the basis Figure 5 A schematic longitudinal cross-section of the cover; and

[0028] Figure 7 Show the basis Figure 4 Cross section of the drive unit. DETAILED DESCRIPTION

[0029] Figure 1 A perspective view of a flying object 1 according to an embodiment of the invention is shown. The flying object 1 comprises a fuselage 2 with a longitudinal axis L. The fuselage 2 is designed aerodynamically, in particular with regard to cruising flight in the direction of the longitudinal axis L.

[0030] The flying object 1 has a plurality of drive devices 10 on the fuselage 2. Each of the drive devices 10 is rotatably mounted about a transverse axis Q arranged at an angle, for example, perpendicularly, to the longitudinal axis L. The drive device 10 has a rotatable turbine 20 and a housing 30. The rotatable turbine 20 has an axis of rotation R, about which, for example, a propeller can rotate. The turbine 20 can thereby generate a propulsion force, which can be used to drive the flying object 1. Due to the rotatability of the drive device 10 about the transverse axis Q, the axis of rotation R can also be rotated about the transverse axis Q. This allows the direction of the propulsion force generated by the turbine 20 to be adjustable.

[0031] The cover 30 is constructed as an annular wing and Figures 4 to 7 Describe in more detail.

[0032] The flying object 1 can be driven and controlled by the rotatability of the drive device 10 and the propulsion force that can be generated by the turbine 20. As a result, the flying object 1 can take off and land vertically.

[0033] In this example, four drive devices 10 are arranged around the fuselage such that two drive devices 10 are each arranged at a different position in the direction of the longitudinal axis L than the other drive devices 10, and two drive devices 10 are each arranged at a different position transverse to the longitudinal axis L than the other drive devices 10. This achieves high stability and / or controllability of the flying object 1, both with respect to rotations of the flying object 1 about axes transverse to the longitudinal axis L and with respect to rotations of the flying object 1 about the longitudinal axis L. The drive devices 10 can be arranged in various ways; for example, the respective transverse axes Q of the drive devices can be parallel to one another or at an angle. The number of drive devices 10 can be adapted to the shape, power, and size of the flying object 1.

[0034] An additional cover 30, which does not include the turbine 20 (not shown), can also be arranged rotatably around the fuselage 2 about the transverse axis Q in order to provide additional control and / or stabilization during flight. The flying object 1 can have a drive 10 and a cover 30, in particular without the turbine 20, wherein the cover 30 is mounted on the fuselage 2 rotatably about the transverse axis Q, similar to the drive 10. The cover 30, in particular without the turbine 20, can generate lift solely through its annular wing shape and thus act like a wing, and / or contribute to the control of the flying object 1 through the rotatability of the cover 30.

[0035] Advantageously, the cover 30 is rotatably mounted about its longitudinal axis L. The rotatable mounting of the cover 30 about its longitudinal axis L allows the lift generated by the cover 30 during flight by the airflow around it to be directed in a targeted manner in a direction that can be adjusted by rotating the cover 30 about its longitudinal axis L. For example, the flying object 1 may tend to adopt a tilted attitude due to a failure or shut-off of the turbine 20, since the lift on the side of the failed or shut-off cover 30 is reduced. If the failed or shut-off cover 30 is correspondingly rotated about the longitudinal axis L, it can generate lift by the airflow around it, which counteracts the tilted attitude and advantageously compensates for it. In this way, the flying object 1 can be brought into a stable descending flight.

[0036] Even without being driven by the turbine 20 , the flying object 1 can glide by the lift of the cover 30 , which leads to a further improvement in the cruising range, using the existing kinetic energy of the flying object 1 for further forward movement and ensuring a fail-safe function in the event of a loss of propulsion.

[0037] Due to the fact that the flying object 1 can take off and land vertically and fly in horizontal flight in an energy-efficient manner, the flying object 1 can be used, for example, as a flying taxi for transporting goods and / or people. The flying object 1 requires only very small landing and take-off surfaces, does not require complex infrastructure, and can be implemented with or without a pilot (i.e., autonomously).

[0038] exist Figure 1 In the example shown in , the drive device 10 is oriented so that the axis of rotation R is oriented perpendicular to the ground. As a result, the drive device 10 can generate a propulsion force in the vertical direction and the flying object 1 can thereby perform an ascending flight and / or a descending flight. By rotating the drive device 10 around the corresponding transverse axis Q, different feasible solutions are obtained for causing the flying object 1 to hover in space and / or accelerate in the flight direction. By swinging or rotating the drive device 10, an acceleration in the flight direction and / or a change in the flight direction can be generated. By rotating the drive device 10 around the corresponding transverse axis Q, fast cruising flight can be achieved with a low power requirement, see Figure 2 Here, the annular wing-shaped cover 30 generates lift during flight, which can carry the entire flying object 1.

[0039] Figure 2 Show Figure 1 shows a side view of an aircraft 1. In this example, the aircraft 1 is in cruising or horizontal flight. Specifically, the drive unit 10 is oriented so that the axis of rotation R is substantially parallel to the longitudinal axis L. This allows the drive unit 10 to generate propulsion in the horizontal direction or along the longitudinal axis L. The drive unit 10 is rotated 90° about its respective transverse axis Q relative to the orientation provided for takeoff and / or landing. The shroud 30 is responsible for aerodynamics, while the turbine 20 generates propulsion.

[0040] During cruising flight, the housing 30 of the drive device 10 generates lift solely through its annular wing shape, which lift keeps the flying object 1 at the desired altitude and / or supports this.

[0041] If turbine 20 is deactivated (e.g., shut down or fails), flying object 1 can be further moved forward and landed reliably by gliding using lift-generating annular wing-shaped cover 30. This applies even if all electronic aids were to fail, since flying object 1 is stabilized by the aerodynamic shape of cover 30. The design and fastening of cover 30 to fuselage 2, as well as the design and fastening of the advantageous bulge arranged around air inlet opening 12 on the front side of cover 30, ensure that flow separation does not occur.

[0042] Figure 3 Show Figure 1 and 2 FIG. 1 shows a top view of the flying object 1. In this example, the flying object 1 is in ascending flight and / or descending flight. That is, the drive device 10 is oriented so that Figure 3 The rotation axis R, which is not shown in the drawing and extends into the plane of the paper, is oriented substantially vertically and in this example perpendicularly to the longitudinal axis L. As a result, the drive device 10 can generate a propulsion force in the vertical direction or in a direction perpendicular to the longitudinal axis L.

[0043] The annular wing-shaped cover 30 of the drive device 10 and the advantageously shaped flow deflectors 37 assist in controlling the flying object 1 in ascending and / or descending flight and provide advantageous aerodynamics with low flow resistance.

[0044] By switching on the drive 10, the specially aerodynamically shaped blades 24 of the turbine 20 are set into rotation about the axis of rotation R and a downwardly directed force is generated, which lifts the flying object 1 vertically upward. By means of the different rotational speeds of the four independently controllable drive 10 and / or the orientation of the axes of rotation R of the four independently controllable drive 10, a change in flight attitude, i.e., a change in the attitude of the flying object 1, is generated, which enables flight in all directions and specifically orients the flying object and / or stabilizes it against roll, pitch, and / or yaw.

[0045] Figure 4 The drive device 10 is shown in longitudinal section. The drive device 10 has a turbine 20 and a housing 30. The turbine 20 has a propeller with wings 24 and a shaft 22. The wings 24 are held on the shaft 22 and the shaft 22 is rotatably supported about an axis of rotation R. As a result, the wings 24 can rotate about the axis of rotation R and the turbine 20 can generate Figure 4 The arrows in FIG. 8 indicate an air flow which results in a propulsion force with which the flying object 1 can be driven.

[0046] The drive device 10 can be rotated so that the axis of rotation R can be rotated about the transverse axis Q. This allows the direction of the propulsive force that can be generated by the drive device 10 to be determined. In this embodiment, the transverse axis Q and the axis of rotation R intersect in the region where the wings 24 are held on the shaft 22. However, in other embodiments, the transverse axis Q can be displaced and / or rotated relative to the transverse axis Q shown.

[0047] The housing 30 has an air inlet opening 12 and an Figure 4The air inlet opening 12 and the air outlet opening 13 are arranged at opposite ends of the cover 30 along the axis of rotation R. Through the air inlet opening 12, the air flow can enter the drive device 10, flow through the drive device 10, and be discharged at the air outlet opening 13. The front air inlet opening 12 can be shaped in a convex manner to accelerate the air mass flow, especially within the cover 30, and at the same time achieve a weight increase in the front part, which has a positive impact on the inherent stability. If flow separation occurs during slow flight, the cover 30 can be tilted forward, and the flying object 1 can remain stable and controlled in the air.

[0048] The turbine 20 is arranged in the region of the air inlet opening 12. The housing 30 has a substantially cylindrical section 31 extending along the axis of rotation R and coaxially surrounding the turbine 20.

[0049] The cover body 30 is Figure 5 and Figure 6 The geometry explained in more detail makes it possible to minimize unnecessary turbulence and flow resistance for the air flowing around the shroud 30 and to generate lift that supports the flight characteristics of the flying object 1 .

[0050] Figure 5 Shown as Figure 4 , a side view of a housing 30 of a drive device 10 is shown in FIG, wherein a turbine 20 with an axis of rotation R can be coaxially arranged in a cylindrical section 31. The housing 30 has its own longitudinal axis through the cylindrical section 31, along which the cylindrical section 31 extends and which, for simplicity, will also be referred to below as the axis of rotation R. The housing 30 can also be attached to the fuselage 2 for steering, controlling, and / or stabilizing the flying object 1 without the drive device 10.

[0051] Starting from the essentially cylindrical section 31, the hood 30 tapers along the axis of rotation R from the air inlet opening 12 to the air outlet opening 13 or to the end section of the hood 30 formed by two flow deflectors 37, which particularly advantageously have an opening angle A of 115°. The opening angle A can be defined here by the angle between the two flow deflectors 37 from their common beginning to the respective top of the flow deflectors 37. An opening angle A exceeding 90°, and advantageously 115°, generates a higher lift, especially during cruising at, for example, 200 km / h, than a hood 30 without flow deflectors 37.

[0052] The outer side 32 of the cover 30 has a first section 33 extending parallel to the axis of rotation R and a second section 34 extending parallel to the axis of rotation R. The first section 33 is arranged diametrically opposite the second section 34. The first section 33 has a greater curvature than the second section 34. As a result, a higher speed of the air flowing around the cover 30 is achieved in the first section 33 than in the second section 34. As a result, a lower pressure is generated on the upper side of the cover 30, i.e. in the first section 33, than in the second section 34, whereby a lift force is generated (Bernoulli effect), see also Figure 4 The lift thus obtained advantageously replaces the use of conventional wings. The geometric structure of the cover 30 and the annular wing shape largely eliminate the induced drag at the wing tip due to the lift, which leads to increased efficiency.

[0053] In the region of the first section 33, a recess 36 is provided, which in particular reduces the flow resistance within the cover 30. The recess 36 extends from the essentially cylindrical section 31 to a flow deflector 37. In its design, the lift cover 30 has two flow deflectors 37 in the rear section, which, due to different pressure ratios between the top and bottom of the cover 30, result in a controlled pressure balance in order to counteract or even out any resulting lift resistance.

[0054] The cover 30 can be manufactured using all conventional manufacturing methods and materials used in aviation.

[0055] Figure 6 Show the basis Figure 5 Schematic longitudinal section of the housing 30. The housing 30 has an inclined and curved end side 35. In this example, the end side 35 is the end side of the housing 30 at which the air outlet opening 13 is provided. Thus, the curved end side 35 is arranged downstream of the turbine 20 when the drive device 10 is in operation.

[0056] The end side 35 of the cover 30 has a recess 36 and two flow deflectors 37 protruding along the rotation axis R. In other embodiments, only one flow deflector 37 and / or no recess 36 may be provided. The end side 35 is inclined and curved, as also in Figure 5 As can be seen in FIG, the aerodynamics of the cover 30 are thereby advantageous.

[0057] Figure 7 Show the basis Figure 4The cross section of the drive device 10 is shown. The cross section shows the turbine 20, which is coaxially enclosed by a cylindrical section 31 of a housing 30. In the example shown, the turbine 20 is designed as a propeller with a shaft 22 and blades 24 and is to be understood purely as an example. Any turbine 20 that converts chemical or electrical energy into kinetic energy, for example in the form of propulsion based on an air flow, can be used. In particular, alternative fuels, CO2-free drives, and renewable energy can be used to drive the turbine 20.

[0058] List of reference numerals:

[0059] 1 Flying Object

[0060] 2 Body

[0061] 10. Drive unit

[0062] 12 Air inlet opening

[0063] 13 Air exhaust opening

[0064] 20 turbines

[0065] 22 Axis

[0066] 24 Wing

[0067] 30 hood

[0068] 31 columnar segments

[0069] 32 outside

[0070] 33 First Segment

[0071] 34 Second Section

[0072] 35 end side

[0073] 36 recess

[0074] 37 Flow Exporter

[0075] A Opening angle

[0076] L longitudinal axis

[0077] Q Horizontal axis

[0078] R Axis of rotation.

Claims

1. A flying object (1) capable of vertical takeoff and landing, comprising - a fuselage (2) having a longitudinal axis (L), and - a plurality of covers (30) arranged on the fuselage (2), wherein: - at least one of the covers (30) is rotatably supported about a transverse axis (Q) arranged at an angle to the longitudinal axis (L), and wherein, The flying object (1) comprises at least one drive device (10) having a rotatable turbine (20) and one of the covers (30), wherein: - said rotatable turbine (20) has an axis of rotation (R) rotatable about said transverse axis (Q), and The housing (30) has a substantially cylindrical section (31) extending along the axis of rotation (R), wherein: The cylindrical section (31) coaxially surrounds the turbine (20), characterized in that - the cover (30) is configured as an annular wing, wherein: The cover (30) has a cover longitudinal axis, and the cover (30) is rotatably supported about the cover longitudinal axis.

2. The flying object (1) according to claim 1, characterized in that The cover (30) is capable of rotating at least 80° around the transverse axis (Q).

3. The flying object (1) according to claim 2, characterized in that The cover (30) is rotatable around the transverse axis (Q) by at least 90° and / or 360°.

4. A flying object (1) according to any one of the preceding claims, characterised in that A plurality of covers (30) are arranged around the fuselage (2) such that at least one cover (30) is arranged at a different position than another cover (30) in the direction of the longitudinal axis (L) and / or at least one cover (30) is arranged at a different position than another cover (30) transversely to the longitudinal axis (L).

5. A flying object (1) according to any one of the preceding claims, characterised in that The flying object (1) has at least two drive devices (10), and at least two turbines (20) are arranged to rotate in opposite directions.

6. A flying object (1) according to any one of the preceding claims, characterized in that The flying object (1) has at least three covers (30).

7. The flying object (1) according to claim 6, characterized in that The flying object (1) has four covers (30).

8. A flying object (1) according to any one of the preceding claims, characterised in that The flying object (1) has an annular wing-shaped cover (30) which is rotatable about a transverse axis (Q) extending transversely to the longitudinal axis (L) and does not have a turbine (20) arranged therein.

9. A cover (30) for a flying object (1) capable of vertical takeoff and landing, wherein: The cover (30) has a substantially cylindrical section (31), wherein a turbine (20) having an axis of rotation (R) can be coaxially arranged in the cylindrical section (31), characterized in that the cover (30) is configured as an annular wing and the cover (30) has a receiving device, which is configured to support the cover (30) on the fuselage (2) of the flying object (1) so that it can rotate around a transverse axis (Q), wherein the cover (30) has a cover-longitudinal axis and the cover (30) is supported so that it can rotate around the cover-longitudinal axis.

10. The cover (30) according to claim 9, characterized in that The cover (30) has a cross section that tapers along the rotation axis (R), the cover (30) has an inclined and / or curved end side (35) and / or the end side (35) of the cover (30) has at least one recess (36) and / or at least one flow deflector (37) protruding along the rotation axis (R).

11. The cover (30) according to claim 10, characterized in that: The cover (30) has two flow deflectors (37) which project forward at an angle of 60° to 130° relative to each other.

12. The cover (30) according to claim 11, characterized in that The two flow deflectors project forwardly at an opening angle of 75° to 120° relative to one another.

13. The cover (30) according to claim 12, characterized in that: The two flow deflectors project forward at an opening angle of 115° relative to one another.

14. The cover (30) according to any one of claims 9 or 10, characterized in that: The outer side (32) of the cover (30) has a first section (33) extending parallel to the rotation axis (R) and a second section (34) extending parallel to the rotation axis (R), wherein the first section (33) has a greater curvature than the second section (34).

15. The cover (30) according to claim 14, characterized in that The first section (33) and the second section (34) are arranged diametrically opposite each other.

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