DE102008044461A1 - Design principle and method for the construction of small aircraft - Google Patents

Abstract

The invention relates to a construction principle and a method for the construction of small aircraft, which are modularly constructed of individual components and allow efficient and cost-effective production of the components and a simple construction of aircraft with the flight principles surface aircraft, gyro, Trike and Paratrike. They are composed of: a uniform, molded body (1) in a closed, stable lightweight construction with only functional openings, comprising seats, dashboard, elements of the control and base elements of the electrical / electronics, as a rear end a partition (26) between the cabin and a Engine compartment and a plurality of externally accessible flanges (17, 18, 21) for receiving the necessary components, wherein a flange can also accommodate a plurality of components and covers (15, 19) of flanges for non-essential in small aircraft flight principles components; on the partition wall (26) of externally located motor with or without gearbox (24), tanks, parts of the control and parts of the electrical / electronic; The same principles apply to individual components necessary for small aircraft of all flight principles (2, 3, 4, 9, 10) and single components designed on the same principles, which are necessary for small aircraft in one or more flight principles. The other individual components are: nose wheel fairing (2), bonnet upper part (3) or ...

Description

The The invention relates to a construction principle and a method for Construction of small aircraft, the modular of individual components are constructed and suitable for mass production.

From the publication DE 10 2005 056 547 A1 is an aircraft design known 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 further aircraft ground assemblies 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. This aircraft design is not suitable for small aircraft.

It is 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. The 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. The multifunctional fastening device at least three articulation points for selectively securing the different wing structures paraglider, fixed wing, kite or rotor blades are created for a gyroscope. The UL aircraft with these cockpit are very simply equipped, do not achieve good aerodynamic properties and have no appealing external shape.

Of the Invention is based on the problem, a design principle and to propose a method of constructing small aircraft, the good aerodynamic properties, efficient and cost-effective Production of the components and a simple assembly and conversion of Aircraft with different flight principles at appealing Allow shape design.

The Problem is inventively by the features of claims 1 and 16 solved. further developments The invention are defined in the dependent claims described. According to the construction principle of the invention Small aircraft of different flight principles are modular built from uniformly designed individual components. The different Small aircraft have a uniform, shapeshifted Basic body in closed, stable lightweight construction with only functional openings, as a rear conclusion one Partition between cabin and engine compartment and several from the outside accessible openings / flanges for receiving the necessary components, with a flange also accommodate several components can. Flanges for smaller aircraft Flight principles unnecessary components get a cover. The construction principle according to the invention comprises individual components designed according to the same principles, for small aircraft of all flight principles and after same principles designed individual components that for small aircraft one or more flight principles necessary. According to the invention, the base body also seats, dashboard, parts of the controller, parts of the electrics / electronics and on the partition from the outside a motor with or without Gearboxes, tanks, parts of the control system and parts of the electrics / electronics on. If required, more equipment can be added be arranged, these being differently equipped and some may be outsourced to other components, like the tanks in the main body or the wings.

In Embodiment of the invention includes the externally accessible Area of the unitary body in the back Area below a flange for a main landing gear, in the rear Area above a coverable opening for one Mast with a flange for a mast fairing or a upper bracket for a propeller protection ring, and in the side, lower area right and left a coverable flange for the wings and at least one tail arm with a Surface transition or at least one tail arm or at least one cover or at least one lower holder for the propeller protection ring. There can be more Flanges may be arranged to separate each component individually To attach flange.

In a further embodiment of the invention The individual components include a nose wheel fairing, a bonnet upper and lower part, a canopy closed, control arms with surface connection and control arms without surface connection, a propeller protection ring with bracket, a nose wheel, a main landing gear, a tail, a windshield open, at least one mast with mast fairing for a gyrocopter, at least one pole with mast fairing for a trike, at least one mast for a paratrike, a cover for a trike, wings and a cover for the mast fairing. It can also be arranged additional components. Skids can be used for take-off and landing on snow and ice, and floating bodies for the landing gear.

To constructed according to the invention small aircraft have opposite The prior art has a number of advantages. As a result of that essential components for small aircraft different Flying principles are used is a manufacture of these components in larger quantities and therefore one efficient and cost-effective production possible. The components designed according to the same principles enable one simple assembly and conversion of a small aircraft from one in a different flight principle and easy replacement of components. Small aircraft according to the construction principle according to the invention have good aerodynamic properties with attractive design. The invention is based on four embodiments explained in more detail. The accompanying drawings demonstrate:

1 : Aircraft, 3-axle, closed, right front view

2 : Aircraft, 3 axles, open, front view right

3 : Gyrocopter, closed, without rotor head and without rotor blades, right front view

4 : Gyrocopter, open, without rotor head and without rotor blades, right front view

5 : Trike, without Trike area, right front view

6 : Paratrike, without paraglider, right front view

7a : Body, without engine and bonnets, rear left view

7b : Body, without engine with bonnets, rear left view

7c : Main body, with engine and hood lower part, rear left view

8th : Tail arm and wing connection surface aircraft

9 : Propeller protection ring with bracket Paratrike

10 : Tail unit

11 : Tail arm gyroplane

12 : Cabin hood for closed variants

13 : Bonnet lower part

14 : Nose wheel fairing

15 : Bonnet upper part

The 1 - 6 contain the four basic variants of the small aircraft according to the invention from the different flight principles, a surface aircraft, a gyroplane, a trike and a paratrike. Mixed forms of two flight principles are possible. A gyrocopter with short wings is not shown, but will be explained.

The 1 and 2 show a surface plane, 3-axle, closed and open in the view from the front right. The uniform, shapely body 1 is designed in a closed, stable lightweight construction with only functional openings. As lightweight construction, all known technologies, in particular based on carbon fiber can be used. In the main body 1 are arranged seats, dashboard, tanks, control elements and basic elements of the electrics / electronics. These can be designed differently or can be outsourced to other components, eg. As the tanks in the wings, which is not favorable for replacement or conversion of the wings. At the back of the main body 1 are an engine with or without transmission 24 as well as tanks, elements of the control and basic elements of the electrics / electronics arranged and are upper part of the hoods 3 and lower part 4 covered. The propeller 25 is outside the hoods. The arranged on a motor mount engine and transmission 24 can be different design and performance. Also the propellers 25 can be selected according to the respective requirements. The chassis consists of a nose wheel 9 with a nose wheel fairing 2 and the main landing gear 10 , In the main body 1 is in the rear area above an opening for a mast and a flange for a mast fairing, which with a cover 19 is closed. A hood 3 Upper part closes the engine compartment above and a hood 4 Lower part of the engine compartment down. The wings 16 and tail arms 6 with surface connection are on the flange 17 with the main body 1 connected. In the embodiment, the tail arm 6 with two-armed surface connection as an expedient design, but under various conditions can also be one-armed with middle connection, three or more arms or also have a closed profile. The tail arm 6 with surface connection carries the tail unit 11 , which can be done differently. To 1 The surface plane contains a canopy 5 closed and after 2 a windshield 12 ,

In the 3 and 4 gyrocopters are shown, closed and open, without rotor head and without rotor blades. For the construction of the gyrocopter with the exception of the tail arm 7 , the mast fairing 13 in which a mast is performed with a run at the top end transition to the rotor head with the rotor blades and the missing in the basic design wings and thus also another control arm, the same components as used in the aircraft area. Also the tail arms 7 can be designed, for example, with one arm with center connection, three or more arms.

For certain requirements, a version with short wings is appropriate. Then, instead of the tail arms 7 stabilizer arms 6 necessary with surface connection.

The 5 shows a trike without Trikefläche, in which some components of the aforementioned variants are not required. As on the flange 17 No component needs to be arranged, this one comes with a cover 15 locked. At the flange 18 is a mast fairing 14 fastened in which a mast is performed with an executed at the top end attachment point for a Trikefläche, not shown. In 6 is a paratrike without a paraglider. Opposite the trike falls the propeller protection ring 8th with its holder, which serves to protect the paraglider with its lines. According to the present embodiment are on both sides of the flange 17 a lower bracket 22 , which can also be designed with one arm with center connection, three or more arms, and on the flange 18 an angled upper bracket 23 of the propeller protection ring 8th fastened, wherein in the area above the kink, an attachment point for receiving the lines of a paraglider is executed. The upper bracket 23 may be one or more parts, the multi-part design comprising a mast covering, in which a mast is made with an attachment point for receiving the lines of a paraglider at the top.

The main body 1 without engine and hoods in the view from behind left shows the 7a , Shown is a perspective view of the shapely body 1 in closed, stable lightweight construction with only functional openings and the flanges 17 . 18 and 21 as well as the surface transition 20 for the nose wheel fairing 2 ,

The 7b shows the main body 1 without engine with closed hoods 3 upper part and 4 lower part in the view from the back left.

To 7c contains the basic body 1 a motor with or without gearbox 24 and a hood 4 lower part in the view from the back left. engine and gears 24 are on the partition 26 arranged between the cab and the engine compartment on a motor mount. The partition 26 forms the fire wall. The drive shaft is led out of the engine compartment and carries at its end the propeller 25 ,

For a simple, flying technically unfavorable execution, both the upper 3 as well as the lower one 4 Bonnet or both hoods omitted.

It is also possible engine and transmission 24 to arrange on a motor support on the existing mast, which is on the partition 26 is attached. Thus, a drive module is present, the simple to the body 1 can be attached.

In the 8th to 15 The components are the tail boom and wing connection, airplane propeller protection ring, tailplane with rudder and rudder, tailplane gyroplane, canopy for closed variants, engine hood lower part, nose wheel fairing and bonnet upper part.

The Invention can with the already mentioned advantages for the construction of small aircraft of different flight principles, especially of ultra-light aircraft. By The same components are also retrofit designs Gyrocopter, trike, para-trike to the surface plane possible.

1

body

2

Bugradverkleidung

3

Engine Hood upper part

4

Engine Hood lower part

5

canopy closed

6

tail boom with surface connection for surface aircraft

7

tail boom for gyroplane

8th

Propeller protection ring for Paratrike

9

nose wheel

10

main landing gear

11

tail

12

windshield open

13

mast with mast fairing for gyroplane

14

mast with mast fairing for trike

15

cover for trike

16

wings

17

Flange for control arm 6 and surface transition or for control arms 7 or for cover 15 or propeller protection ring 8th

18

Flange for mast fairing or propeller protection ring 8th

19

cover for mast fairing

20

Surface transition the nose wheel fairing

21

flange for main landing gear

22

lower bracket for the propeller protection ring 8th

23

Upper bracket for the propeller protection ring 8th

24

engine and gear

25

propeller

26

partition wall

QUOTES INCLUDE IN THE DESCRIPTION

This list The documents listed by the applicant have been automated generated and is solely for better information recorded by the reader. The list is not part of the German Patent or utility model application. The DPMA takes over no liability for any errors or omissions.

Cited patent literature

• - DE 102005056547 A1 [0002]
• - DE 10008678 A1 [0003]

Claims (17)

Design principle for small aircraft, which use a basic body for different flight principles, characterized in that small aircraft of different flight principles are composed of: - a uniform, shapely basic body ( 1 ) in closed, stable lightweight construction with only function-related openings, seats, dashboard, parts of the control organs, parts of the electrical / electronic, as a rear closure a partition ( 26 ) between the cabin and an engine compartment and with a plurality of externally accessible flanges ( 17 . 18 . 21 ) for receiving the necessary components, wherein a flange can also accommodate several components and covers ( 15 . 19 ) of flanges for components not required for small aircraft of certain flight principles; - on the partition ( 26 ) externally located engine with or without transmission ( 24 ), Parts of the control system and the electrics / electronics - single components designed according to the same principles, which are necessary for small aircraft of all flight principles ( 2 . 9 . 10 ) and - based on the same principles, individual components necessary for small aircraft of one or more flight principles. Construction principle according to claim 1, characterized in that the externally accessible surface of the unitary body ( 1 ) comprises: in the rear area below a flange ( 21 ) for a main landing gear ( 10 ), in the rear area above at least one coverable flange ( 18 ) for at least one pole with mast fairing ( 13 . 14 ) or at least one upper bracket ( 23 ) for a propeller protection ring ( 8th ), and in the lateral, lower area right and left a coverable flange ( 17 ) for wings ( 16 ) and tail arms ( 6 ) with a surface connection or tail arms ( 7 ) or a cover ( 15 ) or at least one lower holder ( 22 ) for the propeller protection ring ( 8th ). Construction principle according to claim 1, characterized in that the individual components comprise: a nosewheel fairing ( 2 ), a bonnet upper part ( 3 ) and lower part ( 4 ), a canopy closed ( 5 ), Control arms with surface connection ( 6 ), Tail arms ( 7 ), a propeller protection ring ( 8th ) with bracket, a nose wheel ( 9 ), a main landing gear ( 10 ), a tail ( 11 ), a windshield open ( 12 ), a mast with mast fairing ( 13 ) for a gyrocopter, a mast with mast fairing ( 14 ) for a trike, a mast with in the upper bracket ( 23 ) of the propeller protection ring ( 8th ) integrated mast fairing for a para-trike, a cover ( 15 ) for a trike, wings ( 16 ) and a cover ( 19 ) for the mast fairing. Construction principle according to claims 1-3, characterized in that a tail arm ( 6 . 7 ) is one-armed with center connection or multi-arm. Design principle according to claims 1-3, characterized in that a mast one or more arms executed is. Construction principle according to claims 1-3, characterized in that for the wings ( 16 ) and each tail arm ( 6 . 7 ) separate flanges on the base body ( 1 ) are arranged. Construction principle according to claims 1-6, characterized in that a surface aircraft 3achsig from the main body ( 1 ) with a cover ( 19 ) for the non-existent mast with mast fairing, a nose wheel fairing ( 2 ), a nose wheel ( 9 ), a main landing gear ( 10 ), a canopy closed ( 5 ) or a windscreen ( 12 ), the two at the flange ( 17 ) attached wings ( 16 ) and a tail arm ( 6 ) with surface connection, a tail unit ( 11 ), an engine with or without transmission ( 24 ), a bonnet upper part ( 3 ) and a hood lower part ( 4 ) consists. Construction principle according to claims 1-6, characterized in that a gyrocopter from the base body ( 1 ), a nose wheel fairing ( 2 ), a nose wheel ( 9 ), a main landing gear ( 10 ), a canopy closed ( 5 ) or a windshield open ( 12 ), one on the flange ( 17 ) fixed tail arm ( 7 ), a tail ( 11 ), an engine with or without transmission ( 24 ), a bonnet upper part ( 3 ) and a hood lower part ( 4 ) and one on the flange ( 18 ) fixed mast fairing ( 13 ), in which a mast is performed with a run at the top end transition to the rotor head with the rotor blades, there is. Design principle according to claims 1-6, characterized in that a paratrike from the basic body ( 1 ), a nose wheel fairing ( 2 ), a nose wheel ( 9 ), a main landing gear ( 10 ), a windshield open ( 12 ), an engine with or without transmission ( 24 ), a bonnet upper part ( 3 ) and a hood lower part ( 4 ), one on the flange ( 17 ) attached lower bracket ( 22 ) and one on the flange ( 18 ) attached angled upper bracket ( 23 ) of the propeller protection ring ( 8th ) with an attachment point above the break point for holding the lines of a paraglider. Construction principle according to the claims 1-6, characterized in that a trike from the body ( 1 ) with a cover ( 15 ), a nose wheel fairing ( 2 ), a nose wheel ( 9 ), a main landing gear ( 10 ), a windshield open ( 12 ), an engine with or without transmission ( 24 ), a bonnet upper part ( 3 ) and a hood lower part ( 4 ) and one on the flange ( 18 ) fixed mast fairing ( 14 ), in which a mast is guided with a running at the upper end attachment point for a trike surface exists. Construction principle according to claims 1-6, characterized in that a gyrocopter with short wings from the main body ( 1 ), a nose wheel fairing ( 2 ), a nose wheel ( 9 ), a main landing gear ( 10 ), a canopy closed ( 5 ) or a windscreen ( 12 ), the two at the flange ( 17 ) fixed short wings and a tail arm ( 6 ) with surface connection, a tail unit ( 11 ), an engine with or without transmission ( 24 ), a bonnet upper part ( 3 ) and a hood lower part ( 4 ) and one on the flange ( 18 ) fixed mast fairing ( 13 ), in which a mast is performed with a run at the top end transition to the rotor head with the rotor blades, there is. Construction principle according to one of the preceding claims, characterized in that in the basic body ( 1 ) in the region of the flange ( 17 ) a spar box for receiving the spars of the wings ( 16 ) is available. Construction principle according to one of the preceding claims, characterized in that in the basic body ( 1 ) are arranged in the lower region stiffening elements in the longitudinal direction. Construction principle according to one of the preceding claims, characterized in that on the base body ( 1 ) at the back of the partition ( 26 ) between the cabin and the engine compartment an existing mast with an engine mount arranged on a motor and transmission ( 24 ) is attached. Construction principle according to one of the preceding claims, characterized in that instead of the nose wheel ( 9 ) and the main landing gear ( 10 ) Skids or floats are arranged. A method of constructing small aircraft according to claim 1, characterized by the steps of: selecting the small aircraft from the different flight principles, comprising a surface aircraft, a gyroplane, a trike and a paratrike, and hybrid forms of two flight principles; Examination which flanges ( 17 . 18 . 21 ) of a uniform, shapely basic body ( 1 ) are required in closed, stable lightweight construction with only function-related openings and to what extent a cover ( 15 . 19 ) is required; Selection of the engine with or without transmission ( 24 ); Selection of the necessary components of the same design: nose wheel fairing ( 2 ), Bonnet upper part ( 3 ) or lower part ( 4 ), Canopy closed ( 5 ), Control arms with surface connection ( 6 ) or tail arms ( 7 ), Propeller protection ring ( 8th ) with bracket, nose wheel ( 9 ), Main landing gear ( 10 ), Tail unit ( 11 ), Windscreen open ( 12 ), Mast with mast fairing ( 13 . 14 ) and wings ( 16 ); Basic structure of the aircraft with the main body ( 1 ) and selection and installation of the equipment. Method according to claim 16, characterized in that that by replacing fewer components a small-aircraft of a flight principle converted into a small aircraft of another flight principle becomes.