RU2324622C2 - Fuselage of light helicopter - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: fuselage of a light helicopter comprises frame of the middle part, frame of the rear part with a compartment for at least one engine (10), undercarriage, main reducer (28), and also set of reinforcing transverse-longitudinal components of each portion of the fuselage with a covering, whicform an outer contour of a helicopter. The frame of the middle part is assembled of two reinforced ribs (11, 12) and three panels attached to them (13, 14, 15), at that ribs are assembled with their planes inclined to each other so, the distance between the upper portions of the ribs is lower than the distance between the lower portions. Two of the said panels are located in planes close to horizontal? At that one of the panels (13) is located along the full length of the fuselage at the overall crew cabin floor and shipping compartment level; while the second panel (14) is located at the reinforced ribs upper portion levels and is elongated overhang forward from the reinforced ribs and backward from them along the full length of rear portion of fuselage frame; the third panel (15) is made with its length equal to the length of the first panel (floor) and orthogonal connected to it in a lengthwise plane symmetry of a sub floor portion of the fuselage.

EFFECT: invention provides durability and accident safety of design.

5 cl, 8 dwg

Description

The invention relates to the field of aviation and can be used to create the design of the fuselage of helicopters.

There are many designs of helicopter fuselages, the frames of which are made either in the form of beam or shaped structures, such as, for example, in US patent No. 6126113 of 09/21/1998. The fuselage structure is also known, the power (central) part of which is made of panels joined together, forming a multifaceted structure to which the front and rear parts of the fuselage are docked, the power elements of which are a continuation of the panel components of the central part (patent WO No. 00/05130 of 07/14/1999).

The closest in the set of distinctive features is the design of the fuselage of a light helicopter according to French patent No. 2693976, class. IPC В64С 1/12, dated July 22, 1992 (registered with Rospatent No. 2090450, class B64C 27/00, dated September 20, 1997), which was adopted as a prototype. In a known construction, the frame of the middle part of the fuselage is made of predominantly flat panels interconnected among themselves, the outline of most of which follows the contours of the fuselage. The said panels form the transport compartment of the helicopter and are the constituents of the power skeleton of the fuselage.

The bow is attached to the middle part of the fuselage, forming the cockpit and having a common floor level with the transport compartment, the rear frame with the compartment for at least one engine, the chassis, the main gearbox with the rotor mounted on it. Each part of the fuselage contains a set of reinforcing longitudinally-transverse elements with skin, forming the outer contours of the helicopter.

The spatial placement of the panels and their structural implementation in the well-known technical solution of the fuselage imposes a number of restrictions on the operational capabilities of using a helicopter. So, due to the lack of integrity of the space of the volumes of the transport compartment and the cockpit, due to the fragmentation of the space of the transport compartment by the frame panels of the middle part of the fuselage in a helicopter, it is not possible:

- realize the passenger capacity of the helicopter, adequate to the potential internal volumes of the fuselage;

- equip jobs for medical staff so as to provide comprehensive access to the patient lying on a stretcher in order to provide intensive care in flight.

In addition, the presence in the transport (cargo) compartment of one of the containers of the fuel tank located in the ceiling area imposes increased requirements on the structural strength of the compartment, its increased ventilation and the availability of technical inspection of the compartment (see Aviation Rules, part 27, M., 2000 , §27.963, pp. 44-47).

All this complicates the design of the fuselage, increases its weight and, most importantly, reduces the safety for people on board in the event of an emergency landing of the helicopter.

The technical result achieved by the implementation of the claimed invention is the creation of a fuselage of a light helicopter, the design of which is aimed at eliminating the noted drawbacks when performing the operational tasks specified in the prototype, in particular, increasing the passenger capacity of the helicopter, including the possibility of realizing the interior of the transport (cargo) compartment in the “ Coupe-VIP "with shock-absorbing seats.

In addition, it is possible to load a unified medical stretcher into the transport (cargo) compartment along with a transport trolley.

The technical result is achieved by the fact that in the fuselage of a light helicopter containing a mid-frame, formed from interlocking 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 skeleton of the fuselage, to which the bow is docked with the cockpit crew having a common floor level with a transport compartment, rear frame with a compartment for at least one engine, chassis, main gearbox with a mounted and with it a rotor, as well as a set of reinforcing longitudinal-transverse elements of each of the fuselage parts with skin, forming the outer contours of the helicopter, according to the proposed technical solution, the frame of the middle part is made of two frames and three panels docked with them, and the frames are mounted mutually inclined to each other other planes so that the distances between the upper parts of the frames are less than between the lower ones, two of the said panels are located in planes close to horizontal, while one panel p positioned along the entire length of the fuselage at the level of the common floor of the cockpit and transport compartment, the second panel is located at the level of the upper parts of the reinforced frames and is extended cantilevered forward from the reinforced frames and back from them along the entire length of the frame of the rear of the fuselage 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 junctions with the reinforced frames for mounting the main gearbox, and the third panel is made equal to the length of the first panel (floor) and is orthogonally docked with it in the longitudinal plane of symmetry of the underground part of the fuselage, in addition, the frame of the middle part is equipped with a power stand rigidly fixed in the longitudinal plane of symmetry of the fuselage between the front console part of the second panel and the first panel (floor), while the power rack has a box-shaped cross-section and one of the walls is removable for mounting inside its main rotor rods; the frame of the back of the fuselage contains an additional panel, which is installed at some distance below the second panel, is connected by the front end to the adjacent reinforced frame and is joined to the second panel along the perimeter of the sides with at least two arched half-frames, one of which is installed at the rear ends of both panels, and in the plane of the said adjacent reinforced frame between the additional and second panels, a diaphragm is installed, together forming a compartment for a standard equipped I, which is accessed through an aperture made in an additional panel, with the back frame provided with an inclined arched frame installed between the additional panel and the first panel (floor) forming an aperture in the transport compartment of the middle part of the fuselage, and the contour of the inclined arched frame is paired with a longitudinal set and lining with a smooth aerodynamic contour adequate to the surface of the rear of the fuselage.

In addition, the mutual elevation of the second panel over the first (floor) in the area between the reinforced frames and the shaping of the said frames is made with the possibility of placing in the transport compartment at least two rows of seats, including cushioning, and at least two seats in each row, and the opening in the transport the compartment through the inclined arch frame is made with the possibility of loading through it a unified stretcher together with a transport trolley, for which purpose, on the first panel (floor) in the area near the aperture nodes for mounting the receiving device of the mentioned stretcher with a trolley.

The analysis of the prior art by the applicant showed that there are no analogues that are characterized by sets of features identical to all the hallmarks of the claimed technical solution of the fuselage. Therefore, the claimed technical solution meets the condition of patentability "novelty." In addition, the analysis of the prior art did not reveal the popularity of the impact provided by the essential features of the proposed technical solution of the transformations on the achievement of the specified technical result. Based on this, the claimed technical solution meets the condition of patentability "inventive step".

The technical solution is illustrated by drawings, where:

- figure 1 presents a General view of the fuselage of a light helicopter;

- figure 2 - the frame of the fuselage assembly;

- figure 3 is a fragment of the design of the frame of the middle part with a power rack;

- figure 4 is a cross section of the bottom of the fuselage;

- figure 5 shows the placement in the fuselage of shock-absorbing seats;

- figure 6 - the implementation of the interior of the transport compartment in the variant "Coupe-VIP" with shock-absorbing seats of increased comfort;

- Fig.7 - placement in the transport compartment of the medical staff and the patient on a standardized stretcher and loading the said stretcher in conjunction with a transport trolley;

- on Fig - shows a receiving device for loading a standardized stretcher with a transport trolley.

The fuselage of the light helicopter is made of the bow part 1 that is joined together and forms the cockpit 2 with developed frontal glazing 3, the doors 4, the middle part 5, the frame of which forms the transport compartment 6, which is the power skeleton of the fuselage, to which the chassis 7 and the carrier system are attached ( not shown), the rear part 8, in which the compartment 9 is located for at least one engine 10.

The frame of the middle part 5 of the fuselage is made of two reinforced frames 11, 12, and three panels 13, 14, 15 docked with them, made of high-strength composite materials reinforced with metal. The frames 11, 12 are set in mutually accumulated to each other planes so that the distance between the upper parts of the frames is less than the distance between their lower parts.

Two of the three mentioned panels - panels 13 and 14 are located in planes close to horizontal, while the first panel 13 is made along the entire length of the fuselage in the form of a floor having a common level for the cockpit 2 and transport compartment 6, moreover, the perimeter contour of the panel 13 (floor) repeats the outer contours of the fuselage.

The panel 13 (floor) is reinforced with metal profiles 16 with built-in nodes (not shown) for fastening the seats 17, including shock-absorbing ones, of the guides 18 of the receiving device 19 for loading the unified stretcher 20 together with the transport trolley 21, as well as nodes for fastening the transported inside cargo shipping compartment 6 (not shown).

The second panel 14 is located at the level of the upper parts of the reinforced frames 11, 12 and is installed so that it forms a cantilever portion 22 protruding forward from the said frames and back from the frames 11, 12 the panel 14 is extended along the entire length of the frame of the rear fuselage 8. Between the cantilever part 22 of the panel 14 and the panel 13 (floor), a power rack 23 is installed in the longitudinal plane of symmetry of the fuselage, reinforcing the cantilever part 22 of the panel 14. The rack 23 has a box-shaped cross section and one of the sides of the rack is removable (not shown) for mounting inside the rack 23 rods 24 rotor control. The panel 14 is made of a combined design using composite and metal elements.

The surface of the panel 14, facing the floor (panel 13) in the area between the reinforced frames 11, 12 and on its cantilever part 22, is made in the form of a ceiling of the transport compartment 6 with a noise-attenuating panel 25 installed on it. Another, opposite surface of the panel 14 is made fireproof, by attaching to it, for example, a titanium sheet (not shown).

At the junction of the panel 14 with the frames 11, 12 mounted nodes 26, 27 of the mounting of the main gearbox 28.

The third panel 15 is made along the length of an equal panel 13 (floor), is located orthogonal to this panel in the longitudinal plane of symmetry of the underfloor part of the fuselage and is extended to an intersection with the surface that forms the outward contours of the bottom part of the fuselage.

Reinforced frames 11, 12 in the underground part are provided with diaphragms 29, 30, and along the perimeter of the outer contour, said frames are connected by a longitudinal-transverse set (not shown) with a casing 31, which together with the panel 13 (floor) form a fuel container 32 divided by the panel 15 into two fuel compartments 33, 34 of the caisson type.

To ensure the integrity of the fuselage structure, the frame of its rear part 8 contains an additional panel 35, which is installed at some distance under the second panel 14 and is joined with its adjacent reinforced frame 12. The panels 14 and 35 are interlocked along the perimeter of the sides by at least two arched floors frames 36, 37 and a set of longitudinal elements with a working casing (not shown), while the arched half-frame 37 is installed at the rear ends of the said panels 14, 35, and in the plane adjacent to a strong frame 12 between the said panels, a diaphragm 38 is installed, which together form a compartment 39 for standard equipment, access to which is through an opening 40 made in an additional panel 35.

To increase the rigidity of the frame of the back of the fuselage 8 between the additional panel 35 and the panel 13 (floor), an inclined arch frame 41 is installed, which is fixed at the junction of the arched half frame 36 with the additional panel 35 and the reinforced frame 12 with the panel 13 (floor). In addition, the reinforced frames 11, 12 in the plane of the additional panel 35 are interlocked with longitudinal power elements 42, which are a continuation of the power elements (not shown) located along the perimeter of the sides of the additional panel 35.

In the inclined arch frame 41, an opening 43 is organized into the transport compartment 6 of the fuselage, commensurate in size with the doorway of the door 4, which provides increased operational capabilities of the helicopter. In this case, the angular position of the inclined arch frame 41 is selected so that the perimeter of its contour is conjugated with a longitudinal set and covering the rear part of the fuselage 8 with a smooth aerodynamic contour adequate to the surface forming the said part of the fuselage. As a result of this, as is known from experimental studies (see A.K. Martynov, Applied Aerodynamics. M., Mechanical Engineering, 1972, pp. 358-360), the boundary streamlines that form the zone of the turbulent boundary layer in the rear of the fuselage 8 do not lead to increase the effect of ejection from the stagnant region behind the inclined arch frame 41, and consequently, to discharge in the said region, which in turn does not increase the bottom resistance of the fuselage.

Figure 5-8 shows examples of characteristic operational capabilities of the proposed light helicopter. So the mutual excess of the second panel 14 over the first panel 13 (floor) in the area between the reinforced frames 11, 12 and the forming structure of the said frames and their relative position are made in the proposed technical solution so that in the transport compartment 6 it is possible to place at least two rows of seats 17 , including depreciation, and at least two seats in each row (figure 5). In addition, the volume of the transport compartment 6 allows you to implement the interior in the style of "Coupe-VIP" (see Fig.6), equipped with specialized increased comfort chairs 44 and individual tables 45 to them.

The boarding of passengers is carried out through the doorways of doors 4, and baggage (not shown) is loaded through the opening 43 in an inclined arched frame 41.

7-8 shows a variant of the proposed fuselage for an ambulance helicopter. A distinctive feature of the aforementioned fuselage is the possibility of loading through the opening 43 in an inclined arch frame 41 of a standardized medical stretcher 20 together with a transport trolley 21, which does not require the procedure of transferring the patient 46 during the loading process and this increases the mobility of evacuation.

In addition, the volume of the transport compartment 6 makes it possible to place at least two chairs for paramedics 47, 48 next to the stretcher so that comprehensive access to the patient 46 is possible to provide intensive care in flight on board the helicopter.

Possible options for using a helicopter with the proposed fuselage design are not limited to the examples given in this application. At the same time, the architecture for constructing the power frame of the fuselage in the present invention is solved taking into account the safety of people on board in cases of emergency helicopter landings. So the panel 15, located in the longitudinal plane of symmetry along the entire length of the bottom of the fuselage and having a large building height h and an external saber-like contour, repeating the contours of the bottom of the fuselage, plays the role of a kind of “runner” that preserves on the one hand the integrity of the bottom of the fuselage during the destruction of the skid gear 7, and on the other hand, it prevents the “burying” of the fuselage into the ground from the longitudinal Vx component of the speed of emergency impact of the helicopter on the ground. Ensuring greater safety in emergency situations also contributes to the removal of the fuel container 32 outside the habitable compartment - transport compartment 6, while the container 32 itself has increased shock resistance due to the power elements of the fuselage frame (reinforced frames 11, 12, panels 13, 15), which form .

Thus, the concept of the structure of the fuselage carcass, proposed according to this invention, allows to comprehensively solve the issues of ensuring the strength and emergency safety of the structure, operational availability of maintenance of the systems and assemblies located in the fuselage of equipment in various helicopter use cases.

Claims (5)

1. The fuselage of a light helicopter, comprising a mid-frame, formed from predominantly flat panels interlocked with each other, the contour of which follows the outer contours of the fuselage, and forming the transport compartment of the helicopter, which is the power skeleton of the fuselage, to which the bow is docked with the crew cabin, which has a common level floors with a transport compartment, a rear frame with a compartment for at least one engine, and mounting units for mounting the chassis, and the main gearbox with a rotor mounted on it , as well as a set of reinforcing longitudinally-transverse elements of each of the fuselage parts with skin, forming the outer contours of the helicopter, characterized in that the frame of the middle part is made of two reinforced frames and three panels joined with them, and the frames are installed in mutually inclined planes so that the distances between the upper parts of the frames are less than between the lower ones, two of the said panels are located in planes close 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 transport compartment, and the second panel is located at the level of the upper parts of the reinforced frames and is extended cantilevered forward from the reinforced frames and back from them along the entire length of the frame of the rear of the fuselage, said panel is made so that on the front console 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 junctions with the reinforced frames, the main gearbox mounts are installed and, the third panel is made equal to the length of the first panel (floor), and interfaced with it orthogonally in the longitudinal plane of symmetry of the fuselage underground. 2. The fuselage of the light helicopter according to claim 1, characterized in that the frame of the middle part is equipped with a power stand rigidly fixed in the longitudinal plane of symmetry of the fuselage between the front cantilever part of the second panel and the first panel (floor), while the power stand has a box-shaped cross section and one of the rack walls is removable for mounting inside its main rotor rods. 3. The fuselage of the light helicopter according to claim 1, characterized in that the frame of the rear of the fuselage contains an additional panel, which is installed at some distance below the second panel, is connected by the front end to an adjacent reinforced frame and is docked to the second panel along the perimeter of the sides with at least two arched half frames, one of which is installed at the rear ends of both panels, and a diaphragm is installed in the plane of the adjacent adjacent reinforced frame between the additional and second panels, the aforementioned panels and the diaphragm together form a compartment for standard equipment, access to which is through an opening made in an additional panel. 4. The fuselage of the light helicopter according to claim 3, characterized in that the back frame is provided with an inclined arched frame installed between the additional panel and the first panel (floor) forming an opening in the transport compartment of the middle part of the fuselage, and the contour of the inclined arch frame is paired with a longitudinal set and skinning with smooth aerodynamic contour adequate to the surface of the rear of the fuselage. 5. The fuselage of the light helicopter according to claim 1, characterized in that the mutual elevation of the second panel over the first panel (floor) in the area between the reinforced frames and the mold-forming frames mentioned above are arranged to accommodate at least two rows of seats in the transport compartment, including cushioning, and how at least two seats in each row, and the opening into the transport compartment through an inclined arch frame is made with the possibility of loading through it a unified stretcher together with a transport trolley, for which the first step Neli (semi-) in the zone of said aperture provided for fastening the receiving nodes for said device with a trolley stretcher.

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