AIRCRAFT

Abstract

The invention pertains to a remote-controlled miniature aircraft with at least one lift surface (17), with at least one pair of propeller drives (12, 13) and with a weight element (20), the position of which can be varied in the longitudinal direction of the miniature aircraft (10) in order to change the center of gravity of the miniature aircraft (10). In order to realize a more compact and more robust construction with improved flying characteristics, the lift surface (17) of the miniature aircraft (10) is arranged above a plane defined by the rotational axes of the propeller drives (12, 13) in order to generate a lifting force for taking off and/or landing from a standstill.

Claims

1. A miniature aircraft comprising: an upper lift surface and a lower lift surface, at least one pair of propeller drives, and a weight element, a position of the weight element can be linearly displaced in a longitudinal direction of the miniature aircraft in order to change a center of gravity of the miniature aircraft, wherein the upper lift surface is arranged above a plane defined by a rotational axis of the at least one pair of propeller drives in order to generate a lifting force, the upper lift surface is arranged above the lower lift surface, in that the miniature aircraft is in a form of a flying wing, and a flight attitude on a longitudinal axis or a vertical axis of the miniature aircraft is adjusted by a difference between rotational speeds of the at least one pair of propeller drives.

2. The miniature aircraft according to claim 1, wherein the upper lift surface and the lower lift surface are integrated into a single closed wing in order to realize a miniature aircraft without a fuselage.

3. The miniature aircraft according to claim 2, wherein the closed wing is a ring wing or a box wing.

4. The miniature aircraft according to claim 3, wherein the upper lift surface, the lower lift surface or the closed wing are rigid, film-like or inflatable.

5. The miniature aircraft according to claim 1, further comprising propellers on the at least one pair of propeller drives arranged in front of or behind the upper and the lower lift surfaces in the longitudinal direction of the aircraft in order to generate an air flow over the upper lift surface or the lower lift surface.

6. The miniature aircraft according to claim 5, wherein the upper lift surface or the lower lift surface between the rotational axis of the at least one of the pair of propeller drives and a maximum wingspan of the propellers and the at least one pair of propeller drives is arranged between the upper lift surface and the lower lift surface.

7. The miniature aircraft according to claim 1, wherein the propellers of the at least one pair of propeller drives are at least partially shrouded by at least one propeller guard in a region of a propeller circumference.

8. The miniature aircraft according to claim 1, wherein the weight element is centrally arranged on the upper lift surface, between the at least one pair of propeller drives spaced a distance from one another and spaced a distance axially symmetrical to a central vertical axis of the miniature aircraft, wherein the weight element is connected to the upper lift surface underneath the upper lift surface such that it can be pivoted about a lateral axis of the miniature aircraft.

9. The miniature aircraft according to claim 8, further comprising a control for controlling the miniature aircraft wherein a flight attitude in the lateral axis can be adjusted by displacement of the weight element.

10. The miniature aircraft according to claim 9, wherein the control means or an energy supply means is integrated or imprinted into the upper or the lower lift surface or into a closed wing.

11. (canceled)

12. The miniature aircraft according to claim 1 wherein the weight element is linearly displaced in the longitudinal direction of the miniature aircraft along its center line or pivoted about a lateral axis of the miniature aircraft by a servomotor or an ultrasonic motor.

13. The miniature aircraft according to claim 7, wherein the weight element protrudes forward beyond the propeller guard in an intended direction of flight.

14. The miniature aircraft according to claim 7, further comprising an antenna integrated into the propeller guard for receiving control signals for remotely controlling the miniature aircraft.

15. The miniature aircraft of claim 1, wherein the miniature aircraft is axially symmetrical to a longitudinal axis and the upper lift surface further comprises a V-shaped section that is axially symmetrical to the longitudinal axis and tapered in the direction of the weight element and a smallest width of the V-shaped section corresponds to a width of the weight element in order to enable the weight element to protrude beyond the upper lift surface when the weight element is pivoted about a lateral axis of the miniature aircraft.

Description

IN THE FIGURES

[0027] FIG. 1 shows a schematic front view of an inventive aircraft,

[0028] FIG. 2 shows a partially sectioned schematic side view of the inventive aircraft according to FIG. 1, and

[0029] FIG. 3 shows a partially sectioned schematic top view of the inventive aircraft according to FIGS. 1 and 2.

DETAILED DESCRIPTION OF THE INVENTION

[0030] FIG. 1 shows a schematic front view of an inventive aircraft or miniature aircraft 10. The aircraft 10 is constructed axially symmetrical about a vertical axis 11 and provided with two propeller drives 12, 13 that respectively each feature a propeller 14. In the exemplary embodiment shown, the propellers 14 are surrounded by a propeller guard 15 in the region of the outer circumference of the propellers 14. A single propeller guard 15 is provided for the propellers 14 of both propeller drives 12, 13 in this case. Alternatively, it would also be conceivable to provide separate propeller guard elements for the propellers 14 of the propeller drives 12, 13, wherein these propeller guard elements may be connected to one another in order to stabilize the construction.

[0031] A closed wing 16 is arranged behind the propeller guard 15 in the front view according to FIG. 1 or referred to the intended direction of flight of the aircraft 10, respectively. In the exemplary embodiment shown, the closed wing 16 is realized in the form of a ring wing 16. The aircraft 10 is constructed without an additional fuselage. The closed wing 16 features an upper lift surface 17 that is arranged above a lower lift surface 18. The height of the closed wing 16 is smaller than the height of the propeller guard 15. In the exemplary embodiment shown, the height of the wing 16 is approximately smaller than the height of the propeller guard 15. In addition, the closed wing 16 is offset downward relative to the propeller guard 15 in comparison with a central, symmetrical arrangement. However, the closed wing 16 does not protrude over the circumference of the propeller guard 15 in this case, but rather remains within this circumference.

[0032] The propeller drives 12, 13 are mounted on an underside 19 of the upper lift surface 17 at a distance from one another and axially symmetrical to the central vertical axis 11. Furthermore, a weight element 20 is centrally arranged on the underside 19. In the exemplary embodiment shown, the weight element 20 is mounted on the underside 19 by means of a pivot joint 21. In this case, the pivot joint 21 makes it possible to pivot the weight element 20 about a lateral axis 22.

[0033] FIG. 2 shows a partially sectioned schematic side view of the inventive aircraft 10 according to FIG. 1. In the exemplary embodiment shown, the weight element 20 protrudes forward beyond the propeller guard 15 in the intended direction of flight in this exemplary embodiment. A lateral surface 27 is respectively arranged on the lift surface ends that face away from one another and extends over the entire chord of the upper and lower lift surfaces 17, 18.

[0034] A schematically illustrated control means 23 is arranged in an exemplary fashion on the lateral surface 27 of the propeller guard 15. In this case, the control means 23 is realized in the form of an antenna 23 that is integrated into the propeller guard 15 and serves for receiving control signals for remotely controlling the unmanned aircraft 10.

[0035] FIG. 3 shows a partially sectioned schematic top view of the inventive aircraft 10 according to FIGS. 1 and 2. A schematically illustrated energy supply means 24 is arranged in an exemplary fashion on the upper lift surface 17. In the exemplary embodiment shown, the energy supply means 24 is realized in this form of a solar module 24.

[0036] The aircraft 10 is axially symmetrical to a longitudinal axis 25. Furthermore, the upper lift surface 17 features a section 26 that is realized axially symmetrical to the longitudinal axis 25. The section 26 is essentially realized in a V-shaped fashion and tapered in the direction of the weight element 20. The smallest width of the section 26 corresponds to the width of the weight element 20 in order to enable the weight element 20 to protrude beyond the upper lift surface 17 when the weight element 20 is pivoted about the lateral axis 22. In the exemplary embodiment shown, the lower lift surface 18 also features a not-shown section 26 in order to enable the weight element 20 to protrude beyond the lower lift surface 18 when the weight element 20 is pivoted about the lateral axis 22.

[0037] The function of the aircraft 10 is elucidated below with reference to FIGS. 1 to 3:

[0038] For example, if the unmanned aircraft 10 should be utilized as a reconnaissance drone, the aircraft is equipped with suitable monitoring means. These monitoring means may form integral components of the weight element 20. The energy required for the operation of the monitoring means, as well as for the control of the aircraft 10, is supplied by accumulators and/or one or more energy supply means 24.

[0039] The aircraft 10 has such dimensions and such a weight that the miniature aircraft 10 can be transported by a single person, for example, in a backpack. The aircraft 10 is controlled by means of a remote control that can be operated by one person. The signals of the remote control are detected by the control means 23 and forwarded.

[0040] In this case, the control is realized in such a way that the aircraft 10 is pivoted about the longitudinal axis 25 and/or the vertical axis 11 by operating the propeller drives 12, 13 with different rotational speeds. Due to the different rotational speeds of the propeller drives 12, 13, these propeller drives generate a different propulsive force such that the aircraft 10 is turned about its longitudinal axis 25 and/or its vertical axis 11. The direction of flight of the aircraft 10 can be controlled in this fashion.

[0041] The weight element 20 is pivoted about the lateral axis 22 of the aircraft 10 in order to control the flying height of the aircraft 10. This causes the center of gravity of the aircraft 10 to shift and the aircraft 10 assumes an ascending position or a descending position in dependence on the pivoting direction.

[0042] Consequently, no control surfaces are required for the control of the aircraft 10 such that the aircraft 10 is particularly robust and a high ground readiness is promoted. Furthermore, it is not required to provide a tail boom such that a compact construction is ensured.

[0043] The propellers 14 that are arranged in front of or, according to an alternative embodiment, behind the lift surfaces 17, 18 and the propellers 14 already conduct air over the lift surfaces 17, 18 with high speed at a standstill. This results in a very slow take-off speed such that the aircraft 10 is able to take off from and land in the hand of a person.

LIST OF REFERENCE SYMBOLS

[0044] 10 Aircraft or miniature aircraft
11 Vertical axis
12 Propeller drive
13 Propeller drive

14 Propeller

[0045] 15 Propeller guard

16 Wing

[0046] 17 Upper lift surface
18 Lower lift surface

19 Underside

[0047] 20 Weight element
21 Pivot joint
22 Lateral axis
23 Control means
24 Energy supply means
25 Longitudinal axis

26 Section

[0048] 27 Lateral surface