WO2010025860A2

WO2010025860A2 - Main body for aircraft

Info

Publication number: WO2010025860A2
Application number: PCT/EP2009/006152
Authority: WO
Inventors: Christine Ahrens-Arnold
Original assignee: Modular Flying Concepts Gmbh
Priority date: 2008-08-25
Filing date: 2009-08-25
Publication date: 2010-03-11
Also published as: WO2010025860A3; DE102008044461A1

Abstract

The invention relates to a main body for an aircraft. In the process, the problem is solved of creating a uniform main body which has good flight characteristics and which is suitable for various flight principles, such as helicopter, gyroplane, fixed-wing aircraft, trike, and paratrike. Such aircraft can therefore be produced efficiently and at low cost. The main body according to the invention comprises only a limited number of openings, through which fastening elements for wings, tail units, paragliders, or the like, and control elements for rudders are guided. Suitable components can thus be installed according to a modular design. The invention is preferably used in small and model aircraft.

Description

Basic body for aircraft

The invention relates to a body for aircraft, which are modularly constructed of individual components and are suitable for mass production.

The document DE 10 2005 056 547 A1 discloses an aircraft construction for industrial mass production. The aircraft construction is modularly constructed from a central aircraft base unit and main aircraft components and further subordinate, aerodynamic mechanical-aerodynamic components. The modular structure system is based on a stable aerodynamic-aerodynamic fuselage base cell to which other aircraft ground units and major aircraft components are movably or permanently coupled. The fuselage base cell is constructed of a structure having a plurality of stable frames on which stably designed mounts are formed for the coupling of further basic structural units and main components. Main components are the wings, the front duck wings, the tail units, the engine gondolas or engines.

Known from the document DE 100 08 678 A1 also a cockpit for UL aircraft with a drive unit. On the cockpit is mounted a multifunctional fastening device with multiple articulation points for selectively securing different wing structures. The cockpit has an open frame construction with a rear landing gear, a nose wheel and a drawbar for transport. The base frame consists of two base tubes which span a substantially triangular plane, wherein the spaced-apart ends of the base tubes are interconnected by a transverse strut. A bottom plate is welded between the base tubes. The basic tubes form together with the obliquely upwardly extending front and rear support tubes and the upper longitudinal members of the open frame construction. The multifunctional fastening device is arranged on the upper longitudinal members of the frame construction. Due to the multifunctional fastening device at least three articulation points for selectively securing the different wing structures Paraglider, fixed wing, dragons or rotor blades created for a gyrocopter. The UL aircrafts with these cockpit are very simply equipped, but do not achieve good aerodynamic properties and have no appealing outer shape.

The invention is based on the problem to propose a body for aircraft, so that they allow good aerodynamic properties, efficient and cost-effective production of the components and a simple construction and conversion of aircraft with different flight principles with attractive design.

The problem is solved by the features of claim 1. Further developments of the invention are described in the dependent claims.

In this context, an aircraft is understood to mean a multiplicity of aircraft and air sports devices with different flight principles, such as, in particular, airplanes, helicopters, gyroplanes, trikes, para-trikes and the like. These can also be designed as ultralight aircraft or model airplanes.

An airfoil aircraft, such as a glider or a powered aircraft, is buoyed by air currents on wings, which are usually rigidly mounted to the right and left of a cockpit. A helicopter is an aircraft that is buoyed and propelled by one or more powered rotors. These act like rotating wings. A gyrocopter, also called gyrocopter or autogiro, is a rotorcraft and is similar in function to a helicopter. However, here the rotor is set in motion not by an engine but by the wind. The lift is generated as in a helicopter by the relative movement of the rotor blade relative to the surrounding air. The propulsion is usually done by a propeller engine or by towing. A pattern available on the market is for example the gyrocopter "MT-03" from the company "AUTO A trike is a three-wheeled motorized hang glider that is weight-controlled, with a wing top mounted above a cockpit by a mast construction such as offered by the company "P & M Aviation" under the model designation "QUIK GT450". A para-trike is similar to the trike described, but instead of a wing, a screen connected by ropes or the like to a cockpit is used A model available on the market is, for example, "GRASSHOPPER-PARA-TRIKE" from UL-Flugzeugbau Quander ".

The invention is based on the following construction principle. After that are

Aircraft of different flight principles built modularly from uniformly designed individual components. The various aircraft have a uniform, shaped body in largely closed, stable lightweight construction with essentially only functionally related openings. These are designed, for example, as flanges. Depending on the selected flight principle, suitable first elements can be connected to the main body, such as wings, tail units, wings, rotary wings, paragliders and the like. These first elements usually also have matching rudder elements, such as transverse, side or elevator or adjustable rotor blades. For controlling these rudder elements there are control means which can be designed mechanically, for example as articulated rods, PushCable, hydraulically, electrically and / or electro-mechanically. In order to be able to assemble the first elements and the control means at the same time, the main body has the openings or flanges.

In a further development of the invention, at least some of the flanges can also be designed in such a way that more than one of the first elements and suitable control means can be mounted on them simultaneously or in succession.

Thus, it is possible, via a provided on the top - with respect to the direction of flight - of the main body flange to mount the following elements: - a mast to which can be attached o a rotor head with rotor blades or - A -

o a paraglider

- a mast fairing

- a rotor head drive that can be guided inside the mast fairing - a propeller protection ring mount.

About flanges, which - related to the direction of flight - right or left at

Base bodies are arranged, can be mounted simultaneously or sequentially: - wings

- Holding elements for a tail unit

- Control system for side, aileron and elevator

- A bracket for a propeller protection ring.

In order to increase the possible uses of the basic body according to the invention, in another embodiment, a further flange is provided, to which either a chassis or runner can be mounted.

There may also be other flanges to attach each of the components, such as first elements, control means and chassis parts, individually to a flange can.

Openings or flanges for components not essential to aircraft of certain flight principles may be provided with a cover to improve aerodynamic properties and the appearance of the aircraft.

For driving the main body or the associated aircraft, a drive unit is provided which drives a propeller or the like. The drive unit consists essentially of an engine that can be configured as an internal combustion engine, such as by the Otto or diesel method, electric motor or as a hybrid of both. This includes appropriate controls and regulations for the operation of the engine as well as the appropriate energy supply, such as fuel tank or battery and other means, for the Operation are necessary. The drive unit may also include a gearbox with suitable control disposed between the engine and the propeller.

The main body has a cabin space in which - except for a model airplane - during operation, at least one pilot and possibly at least one passenger are located. This cabin space can be separated by a partition from the space in which the drive unit or at least substantial parts thereof are housed. In addition, at least parts of the drive unit may be surrounded by an aggregate clothing to the outside.

The drive unit may be attached as a whole or only partially to the partition and / or on the mast.

For certain types of aircraft, such as trike or para-trike, it makes sense to shield the cabin space as far as possible by means of a windshield of environmental influences, such as wind and rain. Gyroplanes and surface aircraft can also be equipped with such a windshield, for example, for cost reasons or to convey a corresponding flight feeling. However, these aircraft types can also be provided with a hood to protect the cabin space even better against environmental influences. Due to the modular design of the body and its associated parts replacement of windshield and canopy is readily possible and can be done as part of the production of the body or subsequently, for example, by a workshop or by the pilot.

In order to make the body both lightweight and aerodynamic in shape, it has been found useful to use fiber composite based materials such as those based on carbon fiber.

The invention also comprises individual components which are designed according to the same principles and which are the same for aircraft of all flight principles and the same Principles designed for single components that are necessary for aircraft one or more flight principles.

If necessary, further equipment elements can be arranged, these being differently equipped and some also outsourced to other components, such as the tanks in the body or the wings.

Aircraft constructed in accordance with the invention have a number of advantages over the prior art. The fact that essential components are used for aircraft of different flight principles, a production of these components in larger quantities and thus an efficient and cost-effective production is possible. Equipped with the same principles, the aircraft can be easily assembled and converted from one flying principle to another, as well as easy replacement of components. Aircraft according to the design principle according to the invention have good aerodynamic properties with appealing design. Due to the components of the same design, conversion versions of gyrocopter, trike, para-trike to surface aircraft are also possible.

The invention will be explained in more detail below with reference to preferred exemplary embodiments. The accompanying drawings show:

Fig. 1: cockpit with propeller drive

Fig. 2: basic body with drive unit Fig. 3: surface aircraft without hood

Fig. 4: tail

Fig. 5: left tail arm for surface aircraft

Fig. 6: surface aircraft with hood

Fig. 7: gyroplane Fig. 8: left tail arm for gyroplane

Fig. 9: Trike

Fig. 10: Para-Trike

Fig. 11: Propeller protection ring with bracket Fig. 12: Mast connection for gyroplane

Fig. 13: Connection of left tail arm for gyroplane

Fig. 14: Connection of left tail arm for wing aircraft

Fig. 15: connection of left wing Fig. 16: left flange with cover.

1 shows a cockpit 10 from the right front, which essentially comprises a main body 12. To this end, a main landing gear is mounted, which mainly consists of two main wheels 14a, 14b and a chassis support designed as a rocker with a right part 16a and a left part 16b, of which only the right part 16a can be seen in FIG. In the front area - with respect to the direction of flight - a nose wheel 18 is mounted, which is at least partially clad by means of a nose wheel fairing 20. In the rear region of the main body 12, a propeller 22 is arranged, which can be set in rotation by means of a drive unit, not shown here and so the

The cockpit or the associated aircraft moved forward by thrust. The drive unit is here surrounded by an aggregate clothing consisting of a lower part 39a and an upper part 39b. Within the body 12, a front seat 24a and a rear seat 24b are installed. Furthermore, a windshield 26 is provided to shield environmental influences, such as driving wind, insects and rain, in the region of the seats 24. The windshield 26 is secured to the body 12 by means known in the art, such as threaded connections, and may be removed if desired. It should be additionally mentioned that the embodiment shown in Fig. 1 has no hood. However, such is possible in principle, as will be explained in connection with other embodiments.

1 also indicates a first flange 28a to which a right wing for a surface aircraft, a right tail arm for a gyrocopter or a part of a propeller protection ring support can be mounted in the preferred embodiments (see FIGS , 7, 10). Analogously, there is a second flange 28b on the left side of the main body 12 (see Fig. 2). The flange 28a is here provided with a cover 29a. The arrangement of flange 28 and its cover 29 is shown in FIG. 16 as an example for the left side shown. In the upper rear region of the base body 12, a third flange 30 is also present. This is used in preferred embodiments for attaching a fairing for a mast, which is needed for example when used as a gyroplane, as a trike or as a para-trike (see Fig. 7, 9, 10).

Similar to the flanges 28, the flange 30 can also be covered by covers. For this purpose, the flanges or their surroundings on the main body 12 are designed accordingly. Essentially, the covers serve to enhance the aerodynamics and aesthetics of the cockpit or associated aircraft. Preferred embodiments of the flanges 28, 30 are shown in Figs. 12-16.

Behind the rear seat 24b there is a partition wall 32 which separates a cabin space 34 from an aggregate space 36. In the first, the seats 24 are for a pilot and a passenger, and in the latter, a drive unit 38 is housed, which can be seen in Fig. 2.

Although not shown in FIG. 1, the cockpit 10 also has conventional means well known to those skilled in the art. These include in particular - instruments such as airspeed indicator, altimeter, variometer, tachometer,

Temperature meter, etc.

- Controls, for elevator, ailerons and ailerons and a power lever for the drive unit 38.

- Communication and navigation equipment, such as radio, transponder, VOR, GPS navigation or the like.

Fig. 2 shows the main body 12 from the rear left with the drive unit 38, to which the propeller 22 is mounted. The drive unit 38 consists essentially of a motor. This is designed here as an internal combustion engine. A four-stroke engine, type Rotax 912 or 914, has proven successful. However, it is also conceivable to provide instead or additionally an electric motor for driving the propeller 22, which is selected according to the drive unit used. The engine or its crankshaft can be connected directly to the propeller 22. It has However, shown that an intermediate gearbox is very beneficial. This can have a fixed gear reduction; However, it is also conceivable a flexible transmission ratio, for example by a centrifugal force control, an automatic transmission with converter, a dual-clutch transmission or the like. The drive unit 38 also has all the necessary ancillaries and other elements that are necessary for operating the engine, such as power generator, battery, fuel supply, ignition and the associated electrical or electronic control units.

The drive unit is arranged in the preferred embodiment on the partition wall 32 on a motor mount, which is not shown. The partition 32 also serves as a fire wall.

The drive unit 38 is unclad in a simple and inexpensive embodiment of the cockpit 10. Thus, a good cooling can be ensured. However, then the drive unit 38 is exposed and also the aerodynamic and aesthetic characteristics of the cockpit are unfavorable. Therefore, in the embodiment of Fig. 2 - as already indicated in Fig. 1 - a two-piece aggregate clothing provided, which consists of an upper and a lower part, of which only the lower part 39a is shown here.

A flange indicated by 28b has a similar function as the flange 28a, but for the left side of the main body 12. In the front region, an element 40 is provided at the bottom of the main body 12, which allows a surface transition to the nose wheel cover 20, not shown here. In addition, a fourth flange 41 can be seen, which is used for mounting the main landing gear 14, 16. This can be quickly removed and grown, which is advantageous for transport or storage of the cockpit 10. In addition, the main landing gear 14, 16 shown in Fig. 1 can be easily replaced, for example, by skids suitable for landing on snow and ice or in the water. Thus, due to the perspective view of FIG. 2, it is readily apparent that the shaped basic body 12 is designed in a closed, stable lightweight construction with essentially only functionally dependent openings and flanges 28, 30 and 41 and the surface transition element 40. To improve the stability with at the same time low use of material, stiffening elements can be arranged in the longitudinal direction in the lower area of the main body 12.

Fig. 3 shows from the front right a surface aircraft, which can be controlled by three axes, namely longitudinal, vertical and transverse axis. Here, the cockpit 10 shown in Fig. 1 is supplemented by some corresponding components. Connected to the first flange 28a (see Fig. 1) is a right transition piece 48a which is connected to a right tail arm 47a. In an analogous manner, a left transition piece 48b and a left tail arm 47b are mounted on the left side. To the transition pieces 48a, 48b, a right wing 42a and a left wing 42b are mounted. The wings 42 have ailerons 43a, 43b, which can be controlled by the present in the cockpit controls via corresponding controls in the flanges 28.

In addition, a tail 44 is provided, comprising a rudder and a rudder 45, a tailplane, a right and a left elevator 46a and 46b and associated trim elements. The tail is fixed to the cockpit 10 by means of the tail boom, which includes the right tail arm 47a, the right hand leg 48a and the left tail arm 47b and the left hand leg 48b. Details of the corresponding connections to the flanges 28a, 28b are shown in FIGS. 14 and 15.

Fig. 4 shows the tail from the front left and Fig. 5 shows the left part of the tail boom, consisting of the tail arm 47 b and the transition piece 48 b. It can also be clearly seen that the transition piece 48b has an opening 50 which can receive the left wing 42b. The right transition piece 48a is designed analogously. Fuel tanks, which are not shown here, are housed in a preferred embodiment within the cockpit 10 behind the partition wall 32. In addition or instead, tanks may also be accommodated in the other components, such as in the wings 42 or in the tail arm 47.

Fig. 6 shows a very similar wing aircraft as in Fig. 3. It differs in that the windshield 26 is omitted and instead a hood 52 is provided. The interior of the cockpit 10 was only hinted at in this figure. The hood 52 and the windshield 26 are part of the

Module concept of the preferred embodiments and can be easily exchanged for each other either by the pilot, a workshop or in the context of production.

FIG. 7 shows a gyroplane from the front right on the basis of the cockpit 10. For this purpose, a mast covering 54 is mounted on the flange 30 via a connecting element 53. This contains in its interior an upper part 55y of a mast and controls 7Oy, which can be seen in FIG. The mast part 55y and the controls 7Oy are connected to a rotor head, not shown, are mounted on the associated rotor blades, which are also not shown here.

The illustrated gyroplane also has the tail unit 44 in this embodiment (see Fig. 4). To mount it a tail boom is provided, which consists of a right tail arm 57a attached thereto right mounting unit 58a and a left tail arm 57b with associated

Assembly unit 58b (see Fig. 8). The mounting units 58 are designed such that they can be attached to the flanges 28. Fig. 8 shows the left part of the tail boom, consisting of the tail arm 57b and the mounting unit 58b.

Since in a gyroplane the tail requires no controllable elevator, the elevator 46 are locked by suitable means. It is also possible to use one instead of the tail 44, which is not at all Elevator includes. Such a tail is cheaper to manufacture and would therefore also cheaper for the customer. On the other hand, such a tail would not be suitable for use in a hydrofoil aircraft, causing corresponding overhead in logistics within a manufacturing facility and limiting the flexibility of the aircraft to various types of aircraft.

The cockpit 10 is furnished in this embodiment with the necessary controls and instruments that are necessary for a gyroplane.

The gyro shown in Fig. 7, the windshield 26, so it is not provided with a hood. However, due to the modular design, the windshield can be removed and instead the hood 52 mounted (see Fig. 6).

In Fig. 9, the cockpit 10 is converted to a trike. For this purpose, the outer mast part 55y with its lining 54 is mounted on the flange 30 via the connecting element 53, which carries a trike surface, not shown. The mast part 55y and its cladding 54 may basically be designed similar, as in Fig. 7. However, can be dispensed with the mechanical controls here. On the masts, the surface, such as a guyed sail, by means of suitable elements, such as ropes, etc. attached via a central universal joint. The control is done by the pilot through a large crossbar. In Fig. 9 it can also be seen that the flanges 28a, 28b are not needed here and therefore are covered by matching covers 29a, 29b.

In Fig. 10, the cockpit 10 is converted to a para-trike, in which the paraglider and its attachment, such as lines and the like, are not shown. The flanges 28, 30 are used here for the mounting of holding elements 60a, 60c and 60b - the latter shown in Fig. 11 - holding a propeller protection ring 62. This serves to protect the paraglider and its attachment before and after the flight, especially during takeoff and landing. At the same time, the holding element 60c serves as a partial lining for the mast part 55y and is preferably designed so that it is angled, from which an area 6Od is defined. The necessary for the para-trike lines for holding a screen are substantially attached to the mast. However, it is also possible that they are partially attached to the area 6Od, which has matching mounting points.

11 separately shows the retaining elements 60b, 60c and 60d attached to the propeller protection ring 62.

Fig. 12 shows a preferred placement of the flange 30 when the cockpit 10 is converted to a gyroplane (see Fig. 7). For this purpose, the outer mast part 55y is mounted on an inner part 55x of the mast by means of a mast coupling 68. The mast coupling 68 may be formed as a clamp, as is well known in the art for the assembly of pipes and masts. This may have matching screw, which are preferably secured by pins. The inner mast part 55x is connected to the chassis support 16 via the flange 41 and is fastened in the region of the unit space 36 by means of suitable elements 72 on the base body 12, for example on the partition wall 32. On the inner mast part 55x, in this embodiment, an aggregate holder 73 is also attached, to which the drive unit 38 can be mounted.

In addition, in Fig. 12 control elements are provided, each consisting of an inner part 7Ox and an outer part 7Oy. These controls 7Ox, 7Oy are connected to each other by means of a connection 71, which is designed here as a rotatable articulated screw.

Thus, if the pilot cockpit 10 is to be converted into a gyroplane in a workshop, the optional cover of the flange 30 is removed and the outer mast part 55y, the outer controls 7Oy and the mast fairing 54 surrounding the parts 55y and 7Oy are mounted there. In the upper part of the parts 55y, 7Oy is not shown here with a rotor head mounted rotor blades. By means of the control elements 70, the pilot can change the longitudinal and transverse inclination of the rotor head.

For the upgrade of the pulpit 10 to a trike or para-trike (see Fig. 9, 10), only the upper mast is necessary. The assembly of the controls 7Oy can therefore be dispensed with.

Fig. 13 shows the loading of the left side flange 28b for the operation of the cockpit 10 as a gyroplane (see Fig. 7). For this purpose, the left structural arm 57b is fastened to the flange 28b, which is shown here still removed, in order to allow an insight into the interior. This preferably takes place in that the assembly unit 58b is inserted in the flange area in the base body 12 and locked there. This locking can be done for example by screw, which are secured by pins. For controlling the rudder 45 controls 74 are provided. These have a first part 74x, which extends within the base body 12 up to the flange 28b. In its area there is a coupling 75, via which a second part 74y can be connected, which extends within the carrier 57b to the rudder 45. The first part 74x is here a rod and the second part 74y is a pushcable.

FIGS. 14 and 15 show the equipping of the left side flange 28b for operation as a surface aircraft (see FIGS. 3, 6). For this, the transition piece 48b is provided. At this rear of the tail arm 47b is already attached. This attachment can be fixed or detachable. To control the rudder, the two-part control elements 74x and 74y are provided, which are connected to each other in the region of the flange 28b via the coupling 75. In addition, further two-part control elements 76x, 76y are provided, which are connected to one another via a coupling 77 and serve to control the elevator 46. For the control of the left aileron 43 b, which is located in the left wing 42 b, controls 78 are present. These consist of a first part 78x which extends within the base body 12 into the region of the flange 28b. There is a connection by means of a coupling element 79 to a second part 78y, which runs within the transition piece 48b and opens at the left end (seen in the direction of travel) in a connecting element 8Ox. In this, a counterpart 8Oy can be introduced, which is part of controls that can run inside the left wing 42b and control the left aileron 43b.

For assembly, the transition piece 48b is first inserted into the flange and fastened there. This can be done similarly as with the mounting unit 58b. In a preferred embodiment, it is provided that in the base body 12 is a circumferential groove. Inside the tail arm 47b are located

Attachment points at which the tail arm is pulled to the fuselage. In this operation, the controls 74x and 74y, 76x and 76y, and 78x and 78y are also interconnected. Subsequently, a spar 82b provided on the supporting surface 42b is inserted into the cockpit 10 through the transition piece 48b, whereby at the same time the connecting elements 8Ox and 8Oy are coupled together. The wing is then locked, which can be done for example by screw with suitable splint locks. For secure mounting of the support surface 42b or of the spar 82b, an unillustrated spar box is present in the base body 12 in the region of the flange 28b. This also applies analogously to the right side and flange 28a.

Fig. 16 shows the flange 28b as it is covered by the cover 29b. This is inserted into the opening of the flange 28b and locked by means known per se, such as splint-secured screw.

The preferred embodiments can be modified in a variety of ways or combined with each other, such as:

- Mixed forms of several flight principles are possible, such as a

Gyrocopter with short wings; - The base body 12 may be made in a stable lightweight construction, including all known technologies, such as in particular belong to the fiber composite base; - In the base body 12 may be arranged in the lower region stiffening elements in the longitudinal direction;

- The tail arms 47 and 57 and / or the support for the propeller protection ring 62 may also be one-arm with center port, three or more arms or have a closed profile;

- The drive unit 38 can be arranged as a whole or partially on a support on the existing mast. Thus, a drive module is present, which can be easily attached to the main body 12;

- Instead of a mast 55 and several poles can be provided, with a rotorcraft or gyroplane then several

Rotor heads may be present with associated rotor blades;

- The mast fairing 54 can also be dispensed with, which weight and cost can be saved;

- Each part of the controls 70, 74, 76, 78 may be designed as a coupling rod, pushcable or the like. It is also conceivable to replace at least a part of the control elements by hydraulic, pneumatic, electrical and / or electro-mechanical components;

- The chassis support 16 can be attached to the flange 41 by a screw and controls for controlling the drive-brake can be designed similar to the other controls;

- A special variant of the cockpit 10 may be designed such that a conversion to the surface aircraft by the customer is not provided. For this, the mast can be formed in one piece, so that it is possible to dispense with the coupling element 68, whereby production costs can be reduced. In addition, the flight safety can be increased;

- The transition pieces 48a, 48b may also be designed such that instead of the tail arms 47 first, the wings 42 are fixed or detachably connected to them and only in a further step, the tail arms 47 are mounted. In this case, the transition pieces 48 may also be designed such that they are each part of one of the wings;

- In the base body 12 may in the region of the flanges 28, 30, 41 circumferential grooves and on the components to be mounted thereto suitable attachment points be present, which can be used in the assembly of the components to the base body 12 and fixed there.

LIST OF REFERENCE NUMBERS

10 cockpit

12 basic body

14a, 14b main wheels 16a, 16b chassis carrier

18 nose wheel

20 nose wheel fairing

22 propellers

24a, 24b front, back seat 26 windshield

28a, 28b first, second flange (right, left side flange)

29a, 29b Cover for right and left side flange

30 third flange (for mast, etc.)

32 Partition wall 34 Cabin space

36 aggregate room

38 drive unit

39a, 39b lower, right part of the aggregate clothing

40 transition element 41 fourth flange (for main landing gear)

42a, 42b right, left wing

43a, 43b right, left aileron

44 tail

45 rudder 46a, 46b right, left elevator

47a, 47b right, left tail arm for wings

48a, 48b right, left transition piece

50 Opening of transition piece for wings 52 hood

53 Connecting element for mast

54 Mast fairing

55x, 55y inner, outer part of the mast 57a, 57b right, left tail arm for gyrocopter, etc.

58a, 58b Mounting unit for tail unit 57

60a-60d retaining elements for propeller protection ring

62 propeller protection ring

68 Mast coupling 7Ox, 7Oy inner, outer controls for rotor head

71 Connecting element for rotor head control

72 mast holding elements

73 Aggregate holder

74x, 74y inner, outer rudder controls 75 rudder control link

76x, 76y inner, outer controls for elevator

77 Connecting element for elevator control

78x, 78y inner, outer controls for ailerons

79 first aileron control unit 8Ox, 8Oy second aileron control unit (two-piece)

82a, 82b Holm for right, left wing

Claims

claims

Aircraft basic body (12) to which first elements (42, 44), such as wings, rotary wings or the like, can be fastened by means of fastening means (55, 48, 58, 82), so that by suitable selection of the first elements ( 42, 44) aircraft are provided with predetermined flight principles and with control means (70, 74, 76, 78) for controlling rudder elements (43, 45, 46) which allow a flight operation according to the selected flight principle, characterized in that the base body (12) an aerodynamically advantageous shape and includes predetermined openings (28, 30) through which the fastening means (55, 48, 58, 82) and the control means (70, 74, 76) can be guided.

2. main body (12) according to claim 1, characterized in that the fastening means comprise at least one mast (55x, 55y, 68) to which a rotor, a support surface and / or a paraglider can be attached.

3. basic body (12) according to any one of the preceding claims, characterized in that the fastening means comprise a first fastening element (58) by which a tail (44) on the base body (12) can be fastened, wherein the first fastening element (58) is also designed so that it is suitable to receive first control means (74y) for controlling a rudder (46).

4. main body (12) according to any one of the preceding claims, characterized in that the fastening means comprise a second fastening element (48) through which a tail (44) and a support surface (42) can be fixed to the base body, wherein the second fastening element (48) is also designed such that there are first control means (74y) for controlling a rudder (46), second control means (76y) for controlling an elevator (46) and / or third control means (78y, 8Ox) for controlling an aileron ( 43).

5. main body (12) according to any one of the preceding claims, characterized in that a further opening (41) is present, via which a chassis (14, 16) and / or a runner can be attached to the base body.

6. basic body (12) according to any one of the preceding claims, characterized in that at least one of the openings (28, 30, 41) or the environment are designed so that a cover (29) can be attached to the aerodynamically advantageous form of Main body (12) as far as possible to obtain or improve.

7. main body (12) according to any one of the preceding claims, characterized in that a drive unit (38) is present, which drives a propeller (22).

8. main body (12) according to any one of the preceding claims, characterized in that a partition wall (32) is present, which separates a unit space (36) of a cabin space (34).

9. main body (12) according to any one of the preceding claims, characterized in that a windshield (26) and / or a hood (52) are mountable, whereby the cabin space (34) can be protected against environmental influences.

10. main body (12) according to any one of the preceding claims, characterized in that it in stable lightweight construction of materials

Fiber composite base is made.

11. Basic body (12) according to any one of the preceding claims, characterized in that the drive unit is at least partially attached to the partition wall (32) and / or on the mast (55).

12. An aircraft with a base body (12) according to any one of the preceding claims, characterized in that the aircraft is designed as a wing aircraft, a gyroplane, a helicopter, a trike and / or a para-trike.