RU2499742C2 - Freight aircraft protective gear - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: proposed protection device comprises barrier wall arranged between cockpit and freight compartment and means of its attachment to fuselage structural elements and floor rails. Said attachments, part from one of extreme means relative to fuselage elements, can be shifted relative thereto in directions parallel with aircraft crosswise and vertical axes to rule out torsion moment application to floor elements in emergent landing.

EFFECT: better manufacturability, decreased weight.

5 cl, 14 dwg

Description

Technical field

The invention relates to cargo aircraft in terms of means of preventing the consequences of impact of cargo in an accident, for example, during an emergency landing.

State of the art

Analogues of the claimed device are devices according to patents: RF - No. 2117607 and USA - No. 3486723 and No. 3897919.

As a prototype, the protective device described on the Internet site “025. Household, baggage-cargo and rescue equipment ”:“ 3.2. In the zone of the 11th frame, a barrier partition is installed that separates the front lobby from the cargo compartment. ... 3.6. The floor frame of the cargo compartment is being finalized in connection with the installation of the fifth rail along the axis of symmetry of the aircraft and the cargo floor system. The pitch of the holes in the floor rails is an inch. Non-metallic flooring is finalized by sticking a metal sheet and is installed flush with the top surface of the rails. "On the floor beams in the zone of frames, supports are installed under the side supports for pallets with cargo."

Protective device - the prototype as well as the device according to this application contains a barrier wall located between the room for persons accompanying the cargo, from the crew compartment and the cargo compartment, and means for fastening the barrier wall to the power elements of the fuselage and the rails of the cargo floor.

Disclosure of invention

The invention solves the problem of improving the manufacturability and reducing the weight of the design of the protective device of a cargo plane.

The solution to this problem is achieved by the fact that in the patented protective device of a cargo aircraft containing a barrier wall located between the room for persons accompanying the cargo, from the cockpit side and the cargo compartment, and means for fastening the barrier wall to the power elements of the fuselage and the rails of the cargo floor, according to the invention, the means of fastening the barrier wall to the power elements of the fuselage and the rails of the cargo floor (except extreme) made with the possibility of displacement relative to the power elements of the fuselage and rel height of the cargo floor in directions parallel to the transverse Z and vertical Y axes of the aircraft with the exception of the application of torque to the rails of the cargo floor during an emergency landing.

Means of fastening the barrier wall to the power elements of the fuselage can be distributed along the perimeter of the barrier wall facing the power elements of the fuselage

Each means of fastening the barrier wall to the power elements of the fuselage can be made in the form of a thrust adjustable along the length, provided at the ends with ball joints

The means for attaching the barrier wall — except for the extremes relative to the fuselage elements — to the rails of the cargo floor may include a stop fitting mounted on the barrier wall and a mating element fastened to the rail of the cargo floor, while the stop fitting and mating device are made with flat end sites located in planes parallel to the plane formed by the transverse Z and vertical Y axes of the aircraft, and interacting with the possibility of relative mutual displacements in the direction of the transverse Z and / or rtikalnoy Y axes plane.

In the means of fastening the barrier wall to one of the fuselage end members of the cargo rail of the cargo floor, the stop fitting mounted on the barrier wall and the counter element fastened to the cargo floor rail can be rigidly bonded to each other - according to the translational degrees of freedom - which is realized when using an eye-type connection, and the means of attaching the barrier wall to the other extreme relative to the power elements of the fuselage of the cargo floor rail is made in a similar way, but with the introduction of a gap between the plane eye surfaces, which allows relative relative displacements in the direction of the transverse axis Z of the aircraft.

The introduction of these means prevents the application of forces on the barrier wall due to deformations of the floor and the fuselage power elements during normal operation of the aircraft, as well as the application of torque to the means of fastening the barrier wall to the rails of the cargo floor in the event of an emergency landing. Due to the exclusion of the transmission of torques, an increase in the manufacturability of the manufacture and a decrease in the weight of the structure of the protective device are achieved.

Brief Description of the Drawings

The invention is further illustrated by specific examples of its implementation with reference to the accompanying drawings, which depict:

Figure 1 - Protective device of a cargo plane. General form.

Figure 2 - Node "A" of figure 1

Figure 3 - Node "A" of figure 1 (cargo rail is not shown)

Figure 4 - View along arrow "D" of figure 2

Figure 5 - Section EE of figure 4

Figure 6 - Node "W" of figure 5

Figure 7 - Node "B" of figure 1

Figure 8 - View along the arrow "And" of figure 7

Figure 9 - Section "KK" of figure 8

Figure 10 - Node "L" of figure 9 (shown the device node "B" of figure 1)

Figure 11 - Node "L" of figure 9 (shown the device node "In" of figure 1)

Figure 12 - Node "G" of figure 1

Figure 13 - View along arrow "M" of figure 12

Figure 14 - Section HH of figure 13

The implementation of the invention

The protective device of a cargo plane contains a barrier wall 1 located between the room for persons accompanying the cargo, from the cockpit side (to the right of the barrier wall in figure 1) and the cargo compartment, and means for attaching the barrier wall to the rails 2 of the cargo floor and to the power elements 3 the fuselage.

Means of fastening the barrier wall 1 to the fuselage power elements 3 are made with the possibility of displacement relative to the fuselage power elements 3 in directions parallel to the transverse Z and vertical Y axes of the aircraft, and are distributed along the part of the perimeter of the barrier wall facing the fuselage power elements. Each of them is made in the form of a rod 4 adjustable in length, provided at the ends with ball joints 5.

Means of fastening the barrier wall 1 to the rails 2 of the cargo floor (node "A") are made with the possibility of displacement relative to the power elements 3 of the fuselage and the rail of the cargo floor in directions parallel to the transverse Z and vertical Y axes of the aircraft with the exception of the application of torque to the floor elements during an emergency landing plane.

Wherein:

- Means of fastening the barrier wall to the rails 2 of the cargo floor — in addition to the extremes relative to the power elements of the fuselage — include a stop fitting 6 mounted on the barrier wall 1 and a mating element 7 bonded to the rail 2 of the cargo floor. The stop fitting 6 and the response element are made with flat end pads 8 located in planes parallel to the plane formed by the transverse Z and vertical Y axes of the aircraft and interacting with the possibility (except for the extreme relative to the power elements of the fuselage) of relative mutual displacements in the direction of the transverse Z and vertical y axis of the plane.

- In the means of fastening the barrier wall 1 to one of the fuselage's extreme relative to the power elements rail 2 of the cargo floor (node "B"), the stop fitting 9 mounted on the barrier wall 1, and the response element 10, fastened to the rail 2 of the cargo floor, rigidly - according to the progressive degrees of freedom - fastened together, which is realized by means of a connection such as an eye. Washers 11 are installed between the stop fitting 9 and the counter element 10 to prevent mutual movements in the direction of the aircraft's transverse Z axis.

- The means of fastening the barrier wall to the rail 2 of the cargo floor, which is extreme with respect to the fuselage elements (node “B”), is made in a similar way, but with the introduction of a gap between the flat surfaces of the eye, which allows relative mutual displacements in the direction of the aircraft’s transverse Z axis.

In the case of deformation of the cargo floor rail in directions parallel to the transverse Z and / or vertical Y axes of the aircraft, a relative mutual displacement of the flat end faces of the corresponding stop fitting and the response element will occur, due to which only the force impact directed parallel to the longitudinal axis X will be exerted on the fitting the plane.

Two lateral mounting points (in conjunction with nodes of type “A” and “D”) provide the minimum necessary wall fastening inside the fuselage.

Thus, the invention ensures the absence of transmission of force at the attachment points during deformation of the floor and the fuselage under normal use and the complete absence of bending moment, and transmission of only tensile force to the rails 2 in the event of an emergency landing.

The above solution allows us to solve the problem of reducing the complexity of manufacturing structures and its weight.

Claims (5)

1. The protective device of a cargo plane containing a barrier wall located between the room for persons accompanying the cargo, from the cockpit side and the cargo compartment, and means for attaching the barrier wall to the power elements of the fuselage and the rails of the cargo floor, characterized in that the means for attaching the barrier wall to the power elements of the fuselage and the rails of the cargo floor, in addition to one of the extreme relative to the elements of the fuselage, made with the possibility of displacement relative to the power elements of the fuselage and the rails of the cargo floor in directions parallel to the transverse Y and vertical Z axes of the aircraft with the exception of the application of torque to the elements of the floor during the emergency landing of the aircraft. 2. The protective device according to claim 1, characterized in that the means for attaching the barrier wall to the fuselage elements are distributed along the part of the perimeter of the barrier wall facing the fuselage elements. 3. The protective device according to claim 2, characterized in that each means of attaching the barrier wall to the fuselage elements is made in the form of a thrust adjustable in length, provided with spherical joints at the ends. 4. The protective device according to claim 1, characterized in that the means of fastening the barrier wall to each intermediate rail, except for those extreme relative to the fuselage elements, includes a stop fitting mounted on the barrier wall and a counter element fastened to the cargo rail the floor, despite the fact that the stop fitting and the response device are made with flat end pads located in planes parallel to the plane formed by the transverse Z and vertical Y axes of the aircraft, and interacting with the possibility of tnositelnyh mutual displacement in the transverse direction Z and / or Y axes vertical plane. 5. The protective device according to claim 1, characterized in that in the means of attaching the barrier wall to one of the rail floor of the cargo floor, which is extreme relative to the fuselage elements, the stop fitting mounted on the barrier wall and the counter element fastened to the rail of the cargo floor are rigidly progressive degrees of freedom are fastened together by means of an eye-type connection, and the means of fastening the barrier wall to the rail of the cargo floor, which is the other extreme relative to the fuselage elements, are made with a gap between the flat surfaces of the eye and the possibility of relative mutual displacements in the direction of the transverse axis Z of the aircraft.

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