RU218285U1 - FUSELAGE OF A LIGHT MULTI-PURPOSE HELICOPTER - Google Patents

Abstract

The utility model relates to the field of aviation equipment, in particular, to the fuselages of light multi-purpose helicopters. The technical objective of the proposed utility model is to increase the maximum takeoff weight of the helicopter without a significant increase in the weight of an empty helicopter, as well as the unification of the fuselage structure in terms of installing a skid and wheeled chassis. The technical result achieved by the implementation of the claimed utility model is to improve the flight performance of the helicopter in terms of increasing the maximum takeoff weight, as well as the ability to install both wheeled and skid landing gear without significant design modifications. The noted technical result is achieved by the fact that in the central part of the fuselage containing the floor and ceiling panels interconnected by means of frames, the tail boom, the bow frame, the frame edging the doorway to the cargo compartment, the longitudinal power beams of the ceiling panel, the longitudinal power beams of the panel floor, inclined frame, edging cutout in the rear of the fuselage, a transverse power element is included - a caisson. 1 ill.

Description

The utility model relates to the field of aviation equipment, in particular, to the fuselages of light multi-purpose helicopters.

A helicopter fuselage is known, containing a central structure and connected to it the front and rear structures, the chassis, and the central structure is a support for the main rotor transmission gearbox and at least one engine and contains a load-bearing frame equipped with fuselage outer skin elements, the load-bearing frame is made in the shape of a hexagon formed by interconnected six panels, two of which are the front and rear transverse panels of the frame, the other two are the side panels of the frame, and the remaining two are the upper and lower horizontal panels of the frame (Patent RU 2090450 C1. Helicopter fuselage. - IPC: B64C 27 /00).

A disadvantage of the known fuselage is the presence of a large number of panels of a sufficiently large area, which, taking into account the dimensions of helicopters with a takeoff weight of up to 4500 kg, leads to an increase in the mass of an empty helicopter to the detriment of the useful, commercial weight of the cargo. Also, the power frame formed by the panels does not allow, without significant local reinforcement of the panels, to install various optional equipment, which also leads to a noticeable increase in the weight of an empty helicopter.

Also known is the fuselage of a light helicopter, containing a frame of the middle part, formed from interlocked predominantly flat panels, the contour of which repeats the outer contours of the fuselage, and forming the transport compartment of the helicopter, which is the power frame of the fuselage, to which the bow with the cockpit is docked, having a common level floors with a transport compartment, a rear frame with a compartment for at least one engine, and installation attachment points for the landing gear, and the main gearbox with a main rotor mounted on it, as well as a set of reinforcing longitudinal-transverse elements of each of the parts of the fuselage with skin, forming external contours helicopter, the power frame of the middle part is made of two reinforced frames and three panels docked with them, and the frames are installed in planes mutually inclined to each other so that the distances between the upper parts of the frames are less than between the lower ones, two of the mentioned panels are located in planes close to to horizontal, while one panel is located along the entire length of the fuselage at the level of the common floor of the cockpit and the transport compartment, and the second panel is located at the level of the upper parts of the reinforced frames and extends cantilevered forward from the reinforced frames and back from them along the entire length of the frame of the rear fuselage , the mentioned panel is made so that on the front cantilever section and between the reinforced frames, one of the panel surfaces forms the ceiling of the transport compartment, and on the other surface of the said panel at the junction with the reinforced frames, the attachment points of the main gearbox are installed, and the third panel is made along the length equal to the first panel (floor), and orthogonally docked with it in the longitudinal plane of symmetry of the underfloor fuselage (Patent RU 2324622 C2. The fuselage of a light helicopter. - IPC: B64C 1/00, B64C 27/04).

The disadvantage of this fuselage is the presence of a large number of panels that form the power frame of the helicopter fuselage, which leads, in view of the large area of the panels, to an increase in the weight of an empty helicopter and a decrease in the weight of a payload, commercial cargo.

The closest analogue in terms of technical solution, taken as a prototype, is a helicopter fuselage with a takeoff weight of not more than 4000 kg, containing floor and ceiling panels interconnected by means of frames, and a tail boom. The frame of the bow, the main front frame, the frame, edging the doorway to the cargo compartment, the longitudinal power beams of the ceiling panel, as well as the longitudinal power beams of the floor panel, the inclined frame, the edging cutout in the rear of the fuselage, the ceiling panel, the floor panel are a power frame helicopter fuselage (Patent RU 139933 U1. The fuselage of a light multi-purpose helicopter. - IPC: V64C 27/04).

The disadvantage of the prototype is the presence of the nose frame, which does not fully perceive the load on the helicopter fuselage from the main gearbox and engine, which leads to excessive weight of an empty helicopter and complicates the fuselage manufacturing technology. Also, the presence of a power element in the central part of the fuselage in the form of a frame does not allow to install a wheeled chassis without changing the power circuit of the fuselage due to insufficient shear rigidity of the frame.

The task to be solved by the claimed utility model is to eliminate the frame in the nose of the helicopter for installing the cockpit canopy and to include a transverse power element - a caisson from the right and left sides into the power circuit of the fuselage.

The technical result of the claimed technical solution is: simplification of the assembly of the fuselage in terms of eliminating the shortcomings of the prototype, the possibility of installing both a skid and wheeled chassis, as well as an increase in the maximum takeoff weight of the helicopter without a significant increase in the weight of an empty helicopter.

The essence of the claimed technical solution is a helicopter fuselage containing floor and ceiling panels interconnected by means of frames, and a tail boom, a bow frame, a frame edging the doorway to the cargo compartment, longitudinal power beams of the ceiling panel, as well as longitudinal power beams of the floor panel , inclined frame, edging cutout in the rear of the fuselage, ceiling panel, floor panel are the power frame of the helicopter fuselage, according to the technical solution, transverse power elements are installed in the central part of the fuselage - caissons, in the upper and side panels that perceive loads from the main gearbox and chassis.

The proposed design of the fuselage is illustrated by the figure, which shows the power diagram of the fuselage of a light multi-purpose helicopter. The diagram shows:

1. bottom panel;

2. the first frame of the bow of the bottom panel;

3. second frame of the bow of the bottom panel;

4. third frame of the bow of the bottom panel;

5. fourth frame of the bottom panel;

6. fifth frame of the bottom panel;

7. sixth frame of the bottom panel;

8. longitudinal beam of the lower panel of the bow (right);

9. longitudinal beam of the lower panel of the bow (left);

10. longitudinal beam of the bottom panel (right);

11. longitudinal beam of the bottom panel (left);

12. third frame of the side panel;

13. third frame of the top panel;

14. transverse power element of the side panel - caisson;

15. sixth frame of the side panel;

16. inclined beam of the rear compartment;

17. longitudinal beam of the top panel (right);

18. longitudinal beam of the top panel (left);

19. transverse power elements of the top panel for installing the main gearbox;

20. transverse power elements of the top panel;

21. seventh frame docking with tail boom;

22. transverse power element of the top panel - caisson;

23. top panel.

The main gearbox, landing gear and tail boom are not conventionally shown on the power diagram. The nose section - the cockpit canopy is shown conditionally.

The design of the fuselage of a light multi-purpose helicopter contains: the bottom panel 1, on which the floor panels are located, the frames 2, 3, 4, and the frame 4 of the lower part connects the bottom panel 1 with the top panel 23 and the upper part of the frame 13 through the sidewall of the frame 12.

Frames 5, 6, 7 connect the bottom panel 1 with the top panel 23 at the installation site of the main gearbox and engines.

Longitudinal beams 8 and 9 of the lower panel 1 of the bow receive loads from the equipment of the cockpit (seats, dashboard, controls).

Longitudinal beams 10 and 11 of the bottom panel 1 perceive the load from the chassis (skid or wheeled) and fuel system equipment.

The transverse power element of the side panel 14 - the caisson, installed in the central part of the fuselage, receives loads from the chassis (skid or wheeled) and distributes them over the area of the side panel).

The side panel frame 15 and the inclined beam 16 of the rear compartment frame the cutout of the rear fuselage and are a support for attaching the tail boom.

On the longitudinal beams 17 and 18 of the upper panel 23, the main gearbox of the helicopter is installed.

The transverse power elements 19 and 20 of the top panel 23 are reinforcement for the installation of engines and equipment in the engine compartment.

Butt frame 21 is designed for attaching the tail boom.

The transverse power element 22 - the caisson of the top panel 23, installed in the central part of the fuselage, takes the load from the main gearbox.

The claimed utility model allows:

- equip the helicopter with both wheeled and skid landing gear;

- to increase the maximum takeoff weight of the helicopter up to 4500 kg without a significant change in the empty weight of the helicopter by optimizing the power circuit.

Claims (1)

Helicopter fuselage, containing floor and ceiling panels interconnected by means of frames, and a tail boom, a bow frame, a frame, edging the doorway to the cargo compartment, longitudinal power beams of the ceiling panel, as well as longitudinal power beams of the floor panel, an inclined frame, edging the cutout in the rear part of the fuselage, the ceiling panel, the floor panel represent the load-bearing frame of the helicopter fuselage, characterized in that transverse load-bearing elements are installed in the central part of the fuselage - caissons in the top and side panels, which perceive loads from the main gearbox and landing gear.

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