CZ201778A3 - A tail-standing aeroplane - Google Patents

Abstract

The tilt aircraft has a hull (4) and a pair of wings (5), each having a leading edge (50) and a trailing edge (55), each of the wings (5) being provided with a propeller drive unit on the side of the trailing edge (55) and a plurality of control pads (21, 22, 23) that includes pivotably mounted at least two control tabs (21, 22, 23) to control the direction of air outflow from the propeller drive unit. The control pad assembly (21, 22, 23) is coupled to a control device (20) for controlling the swing of at least one of the control pads (21, 22, 23).

Description

Technical field

Airplanes that are characterized by the ability to perpend and land upright and which, after take-off, move to a horizontal position in which the cruise phase is in progress are commonly referred to as "tipsitters". The basic advantage of this type of aircraft is the ability to vertical take-off and landing without the need for a runway or other special ejection device, while maintaining the possibility of cruise flight as a flatbed, ie utilizing buoyancy force generated on solid bearing surfaces. On tipping aircraft, there is generally no change in the airplane configuration during flight, or when changing flight modes, ie changing the relative position of the powerplanes and the airplane relative to each other, or changing the bearing surfaces relative to the airplane.

BACKGROUND OF THE INVENTION

Several tailsitter airplanes have been developed and tested in the history of aviation and at present, which differ in the layout of the supporting surfaces, the number and arrangement of powerplanes and the way they control their flight in all flight modes. These examples can be found both in the category of manned aircraft and in the field of unmanned aerial vehicles. Different designs have always been motivated by the effort to ensure reliable machine control in all expected flight modes. It is mainly the drawbar (

- stabilized flight mode in the vertical position of the airplane,

- horizontal flight mode in a fixed-wing airplane configuration,

- transition modes between the above two ^ V

- Safe take-off and landing in vertical position.

SUMMARY OF THE INVENTION

The task of ^ tyiWez is to design a tilting airplane that is reliably controllable in all flight modes.

This task is accomplished by a fuselage having a fuselage and a pair of wings, each with a leading edge and a trailing edge, each of which has a propeller-driven propulsion unit and a control pad assembly that includes a pivotably mounted at least two wings on the trailing edge. control pads for *

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controlling the direction of air flow from the propeller drive unit, the control pad assembly being coupled to a control device for controlling the swing of at least one of the control pads.

Preferably, the control pad assembly comprises a tie rod through which the control pads are interconnected to synchronize their oscillation.

It is also advantageous if the swivel axes of the control pads are parallel to the trailing edge of their respective wing.

In a particularly preferred embodiment, the control pad assembly comprises a pair of outer control pads and a centrally arranged control pad therebetween, the leading edge of which is aligned with the trailing edge of the wing.

Preferably, at least one control pad from each assembly has an aerodynamic teardrop shape in cross section from its leading edge to the trailing edge.

The tilting aircraft is preferably further provided with a central propulsion unit arranged in the plane of symmetry of the airplane. This embodiment is particularly advantageous because the central powerplant can be used during take-off and landing to relieve the weight of the airplane in a vertical position, as well as to propel the airplane in a horizontal position, while propeller power units mounted on wings are advantageously used during take-off and landing. optionally in transitions from vertical to horizontal and back, but can be switched off in cruise mode, the propellers of these propeller power units being in the slot between the wing and the control pad assembly.

Also preferably, the propeller drive unit and control pad assembly on the wing are disposed in its proximal area, while in the distal area the wing is provided with a pivotably arranged tilting wing in its distal area to control the airplane's tilt in flight.

Advantageously, the control surface which is arranged closest to the propeller rotation axis of the propeller drive unit arranged on the wing has a length parallel to the trailing edge of the wing, which corresponds to 80-120% of the propeller diameter.

V / O v

It is also advantageous if the propeller of the propeller drive unit is arranged on the wing such that it is adjustable in the switched-off state in alignment with the wing trailing edge and / or in the slot defined by the wing trailing edge and the control pad assembly.

It may also be advantageous to provide the tipping aircraft in its forward region with a pair of additional stabilizing surfaces. Optionally, it may be advantageous to arrange the leading edge of the tilt wing in line with the leading edge of one of the control pads.

Clarification of drawings

An exemplary embodiment of the invention is shown schematically in the drawings, wherein FIG. Fig. 2 is a side elevational view of the flip plane of Fig. 1; Fig. 3 is a plan view of the flip plane of Fig. 1; Fig. 4 is a portion of the flip-wing with control pads; and Figs. an example of a control pad assembly for a tilting aircraft of the invention.

DETAILED DESCRIPTION OF THE INVENTION

As can be seen in particular from FIGS. 1 to 3, an exemplary embodiment of a roll-over aircraft comprises a fuselage 4, on the front of which a pair of front stabilizing surfaces 11 are arranged. duck surfaces ^ and on the rear fuselage 4 pair of wings 5.

At the rear of the fuselage 4 is a central drive unit 7. In the embodiment shown, it is a propeller drive unit, but alternatively a jet engine or other suitable type of drive could be used.

Furthermore, a pair of upright tails 8, each with a upright 9, are attached to each wing 5 to allow the pivoted airplane to be parked / positioned vertically.

Each wing 5 has a leading edge 50 that faces forward in the direction of flight and a trailing edge 55 that faces rearward. Further, a tilting wing 10 is pivotally attached to each wing 5 on the trailing edge side 55 at the distal region of the wing 5 to control the airplane's tilt in flight.

Each of the wings 5 is provided in its proximal region with a propeller drive unit whose propeller 3 is arranged at the trailing edge 55 of the wing.

In terms of flight direction, a propeller assembly 21, 22, 23 is mounted downstream of the propeller 3, the leading edge of which extends substantially parallel to the trailing edge 55 of the wing 5.

Preferably, the assembly comprises at least two control pads 21, 22, 23, in the particularly preferred embodiment shown it includes three, but it is of course possible to use more control pads 21, 22, 23 in the assembly. The control pads 21, 22, 23 are fixed to the wing 5 by means of a holder 12.

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In the preferred embodiment shown, the control pad assembly 21, 22, 23 comprises a pair of outer control pads 21, 23 and a centrally arranged control pad 22 disposed therebetween and extending substantially such that its leading edge is aligned with the direction of flight. In a particularly preferred embodiment, the centrally arranged control surface 22 is aerodynamically shaped, in particular in its central part in the region facing the axis of the propeller 3, it is infinitely slightly extended, as can be seen in particular in Figures 5a and 5b. At the same time, the at least centrally arranged control surface 22 has an aerodynamic teardrop shape in cross-section from its leading edge to its trailing edge, i.e. substantially in cross-section along a plane parallel to the plane of symmetry of the airplane.

All control pads 21, 22, 23 are mounted with the possibility of pivoting about mutually parallel axes, which are preferably substantially parallel to the trailing edge 55 of the wing 5.

In this exemplary embodiment, a control device 20 is connected to the centrally arranged control pad 22 to adjust its inclination. Each of the outer control surfaces 21, 23 is connected by means of a rod 25 to the centrally arranged control surface 22 so that when the inclination of the centrally arranged control surface 22 changes, the inclination of the outer control surfaces 21, 23 also varies. Thus, for example, all control surfaces 21, 22, 23 can be arranged parallel to each other and can maintain parallelism even when the inclination is changed

2Ζ1ΰΗΓ centrally arranged control pads

It will be appreciated that the actuator 20 may be associated with another of the control pads

21, 22, 23. Optionally, more than one actuator 20 may be used to adjust the inclination of the individual control pads separately / independently.

FIGS. 5a, 5b show a control device 20 comprising a four-articulated and a non-articulated device, respectively;

Lever mechanism. However, other types of control are also possible.

Preferably, the swivel axes of the control pads 21, 22, 23 are arranged at their leading edge.

The control pads 21, 22, 23 have leading edges arranged in a plane parallel to the plane of rotation of the propeller 3 of the propeller drive unit arranged on the wing 5, and preferably the lengths of the control pads 21, 22, 23 in their leading edge direction are chosen approximately in perpendicular projection leading edges of control surfaces 21, 22, 23 to the plane of rotation of the propeller 3, these leading edges formed approximately the chord of the circle

For example, in the illustrated embodiment, the centrally arranged control surface 22 has a length substantially equal to the diameter of the circle described by the propeller 3, while the outer control surfaces 21, 23 are shorter and approximately equal to the chord of the circle described by the propeller 3.

considering the chord having the same distance from the center of the circle as the distance between the leading edges of the centrally located control surface 22 and the outer control surface 21. 23

The plane takes off from the position svi§lp, ie from the position in which it stands on the tail tips 9 of the tail surfaces 8 and 2. For the take-off the central power unit 7 is switched on as well as the propeller propeller units on the wings 5.

the output current is vectorized in the plane of symmetry of the airplane by deflecting the control pads 21, 22, 23.

The control of airplane motion / rotation around all three axes in the vertical position of the airplane is ensured by a combination of the thrust changes of the pair of propeller power units arranged on the wings 5 and independent vectorization of their output air flow provided by deflecting control charts 21, 22, 23.

In the horizontal position flight mode, a cruise control unit 7, which is installed in the plane of symmetry of the airplane and which may be a propeller or jet propulsion unit, is utilized. In this mode, the propulsion units on the wings 5 are switched off and their propellers 3 are positioned in alignment behind the trailing edge 55 of the wing 5, respectively. in the slot between it and the centrally arranged control pad 22.

The solution is via aircraft, but can also be used for manned aircraft.

In the illustrated embodiment, an airplane with a pair of front stabilizing surfaces 6 is used, but it is clear that the invention is applicable to other types of aircraft.

In a particularly preferred embodiment described above, the airplane is provided with a central propulsion unit 7 and a pair of propeller propulsion units on the wings 5. However, an embodiment in which the central propulsion unit 7 is not used will be possible.

Especially suitable for unmanned aircraft

A suitable material of the holder 12 and / or the control pads 21, 22, 23 is, for example, a sheet of high-strength aluminum alloys, depending on the aircraft type.

Although a number of exemplary embodiments have been described, it will be apparent to those skilled in the art that other possible alternatives to these embodiments will be readily appreciated. Therefore, the scope of Wynaiez is not limited to these exemplary embodiments, but rather is defined by the definition of the appended claims.

Claims (9)

PATENT CLAIMS A tipping aircraft having a fuselage (4) and a pair of wings (5) each having a leading edge (50) and a trailing edge (55), characterized in that each of the pair of wings (5) is on the side a trailing edge (55) provided with a propeller drive unit and a plurality of control pads (21, 22, 23) comprising pivotably mounted at least two control pads (21, 22, 23) for controlling the direction of airflow from the propeller drive unit; (21, 22, 23) is connected to a control device (20) for controlling the pivot of at least one of the control pads (21, 22, 23). A tipping aircraft according to claim 1, characterized in that the control pad assembly (21, 22, 23) comprises a rod (25) through which the control pads (21, 22, 23) are connected to each other to synchronize their oscillation. A tipping aircraft according to claim 1 or 2, characterized in that the pivot axes of the control pads (21, 22, 23) are parallel to the trailing edge (55) of their respective wing (5). A tipping aircraft according to any one of the preceding claims, characterized in that the control pad assembly (21, 22, 23) comprises a pair of outer control pads (21, 23) and a control pad (22) centrally disposed therebetween, the leading edge of which is in alignment with the trailing edge (55) of the wing (5). A tipping aircraft according to any one of the preceding claims, characterized in that at least one control pad (21, 22, 23) of each assembly has an aerodynamic teardrop shape in section from its leading edge to the trailing edge. A tipping aircraft according to any one of the preceding claims, characterized in that it is further provided with a central propulsion unit (7) arranged in the plane of symmetry of the airplane. A tipping aircraft according to any one of the preceding claims, characterized in that the propeller drive unit and the control pad assembly (21, 22, 23) are disposed on the wing (5) in its proximal region while the wing (5) is in the distal region. provided on its outflow side with a pivotally arranged tilting wing (10) for controlling the airplane's inclination in flight. Tipping aircraft according to any one of the preceding claims, characterized in that the control surface (21, 22, 23) which is arranged closest to the axis of rotation of the propeller (3) of the propeller drive unit has a length in a direction parallel to the wing trailing edge (55). (5), which corresponds to 80fti to 120lti |% of the propeller diameter (3). líz v. v Flip-off aircraft according to any one of the preceding claims, characterized in that the propeller (3) of the propeller power unit is arranged on the wing (5) so that it is adjustable in alignment with the trailing edge of the wing (5) and / or a slot defined by the trailing edge of the wing (5) and a plurality of control pads (21, 22, 23).