RU2500582C2 - Aircraft safety seat - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Safety seat comprises carcass composed of posts, seat pan, suspension assemblies and power absorber. Posts are equipped with guides for box-like power absorber to be fitted thereat and furnished with post guide slots, ears for attachment to carcass posts and plate recesses. Plate other end is secured at suspension assy composed of a slide moving in post guides. Seat is furnished with safety harness and lengthwise adjustment mechanism arranged at seat pan.

EFFECT: simplified design, decreased weight.

2 cl, 8 dwg

Description

Technical field

The invention relates to the field of aircraft, and more particularly to the design of units that complete the cockpit, in particular the design of the seats. The invention can be used in any form of transport, mainly by helicopter.

State of the art

Known energy-absorbing seat of the aircraft according to patent No. RU 2270138, 05.06.2004 year, class B64D 25/04. The energy-absorbing seat of an aircraft (for example, a helicopter) contains a frame including a seat and a back, vertical struts, an upper suspension unit, a lower suspension unit of a frame, two shock absorbers. The lower ends of the uprights are rigidly attached to the helicopter floor. The upper node of the suspension, made in the form of a pair of sliders that are mounted movably on vertical rails. Vertical guides are rigidly fixed to the back. The lower suspension unit is made in the form of a rotary platform, one end mounted in the lower part of the vertical struts by means of a hinge, and the second movable end connected to the middle part of the seat by means of a hinge with shock absorbers. At the same time, shock absorbers with opposite ends are fixed in the upper parts of the uprights, and two sliders are connected to the upper parts of the uprights by means of hinged assemblies. Shock absorbers can be made in the form of articulated sliding rods. The hinge nodes can be made in the form of forks mounted pivotally in the upper parts of the uprights.

The disadvantage of this invention is, increased metal consumption, massive structure. In addition, the energy-absorbing chair is rigidly fixed to the floor of the aircraft, which reduces the performance of the chair.

Known energy-extinguishing seat of a crew member of the aircraft according to patent RU 2154595 from 10/14/1998 Class B64D 25/04. According to the invention, the energy-extinguishing seat of the crew member of the aircraft contains a base with guides on which the body, the locking mechanism, the spring mechanism and the quenching mechanism mounted on the base are supported by upper and lower sliders. The locking mechanism is equipped with spring-loaded pins fixed to the housing. The spring mechanism supports the housing while adjusting the seat height. The mechanism of energy suppression is made in the form of knives mounted on base rails with the possibility of moving along them with a slice of longitudinal protrusions in the grooves of the rails. The base is equipped with side racks. The racks with the lower ends are built into the rails and are connected to them by means of shear pins. The racks are made with holes for the pins of the locking mechanism. Knives are mounted on racks in front of the ends of the rails. The ends of the guides are made with grooves for the sliders. The sliders are placed on the outside of the base and are provided with grooves for racks that are located on the inside of the base. The grooves for the racks are made with longitudinal protrusions located at the ends opposite the cutting edges of the knives. The cylinders of the spring mechanism are fixed with the upper ends on the uprights, and the lower ends on the seat casing.

The disadvantage of this chair design is that the design of energy-absorbing nodes involves working exclusively along the guide racks. The main part of the vertical load from the weight of the person sitting on the chair comes to the middle part of the seat, which is located at a considerable distance in front of the suspension components of the chair frame. This leads to the fact that the frame of the chair experiences additional bending moments. Which, in turn, create additional loads in the horizontal plane, acting on the suspension units of the frame and energy-absorbing elements. This complicates the work of the sliders during the energy-absorbing movement of the chair, limiting the range of angles of possible emergency touchdowns of the helicopter. In addition, the possibility of skewing and jamming of energy-absorbing elements increases.

The closest in technical essence and the achieved effect is "Seating an airplane with energy-absorbing elements" according to patent GB 2397865, class B60N 2/42; B60N 2/427; B64D 11/06; B64D 25/04; F16F 7/12 from 04.08.2004 years. According to the patent, the chair comprises a chair cup, frame, suspension units and energy absorbing units. The chair cup is made in the form of a back and a base attached to it. The frame is made in the form of two parallel vertical racks interconnected by horizontal rods parallel to each other. Horizontal rods are fixed at the ends of the uprights. Racks and rods are made in the form of pipes.

The energy absorbing unit comprises a metal plate and a bending device. The bending device is made in the form of a box-shaped case with rollers installed in it. The metal plate is mounted parallel to the axis of the chair. One end of the plate is mounted on a vertical drain of the frame, and the other on a horizontal rack. In this case, the plate is located in the bending device so that it interacts with all the rollers. The plate may be made of different thickness.

The suspension unit is made in the form of a bracket equipped with a through hole with which it is mounted on vertical struts, eyes and a fastener with which the bracket is mounted on the aircraft wall. With the eyes, the suspension unit interacts with the bending device of the energy-absorbing unit.

During overloads, the suspension unit connected to the bending device moves along the plate mounted on the chair frame, so that the movement of the suspension unit and the bending mechanism causes plastic deformation of the plate. Due to plastic deformation of the plate, energy absorption occurs.

The energy-absorbing device has insufficient reliability, in particular when side loads are applied to the chair.

SUMMARY OF THE INVENTION

The objective of the invention is to develop the design of the energy-absorbing seat of the aircraft, which allows to expand its functionality by maintaining its performance while increasing the range of angles of possible emergency landings. At the same time, simplify its design and reduce its mass.

The problem is achieved in that the energy-absorbing seat of the aircraft contains a frame made in the form of racks, a cup of the chair, suspension units and an energy-absorbing device. The racks are equipped with guides with an energy-absorbing device rigidly installed in each of them. The energy-absorbing device is made in the form of a boxed part, equipped with grooves for the guide racks, eyes for mounting on the frame racks, a niche for mounting the plate. At the other end, the plate is fixed to the suspension assembly. Suspension nodes are made in the form of sliders movably mounted in guide racks. The chair is equipped with a tethered system and a longitudinal adjustment mechanism mounted on the chair cup.

The solution of this problem allows you to expand the functionality of the energy-absorbing chair, maintain its performance and increase the range of angles of possible emergency landings. In addition, this solution to the problem allows us to simplify the design of the energy-absorbing chair and reduce its weight.

Brief Description of the Drawings

The invention is illustrated by drawings, which show:

Figure 1 - chair energy-absorbing aircraft with an installed seat cup, front view;

Figure 2 - chair energy-absorbing aircraft with an installed seat cup, rear view;

Figure 3 - side energy-absorbing aircraft with an installed seat cup, side view;

Figure 4 is a frame of an energy-absorbing chair, side view;

Figure 5 - node A of figure 3;

Fig.6 is a section bB of Fig.5;

7 is a housing of an energy-absorbing element, isometry;

Fig - node energy-absorbing device mounted on the drains, a cut along the axis of the housing of the energy-absorbing device.

Disclosure of invention

The energy-absorbing chair LA contains (Figs. 1, 4) a cup of a chair 1 with a cover and soft elements, a frame 2, suspension units, an energy-absorbing device 3, a tethered system 4 and a mechanism for longitudinal adjustment of the chair.

The frame of the energy-absorbing seat of the aircraft includes two parallel vertical racks 6, 7. Racks 6, 7 are made in the form of a single element. On the front surface along the entire height of the racks made T-shaped guide. The guide is designed for movable installation of the upper and lower suspension nodes in it, as well as for rigid installation and fixing of the energy-absorbing device. Suspension nodes are made in the form of upper 17 and lower 18 sliders. The racks 6, 7 are provided with a groove 19 for installation on the rails 21 rigidly fixed on the floor of the aircraft (Fig. 3). In the upper part of the uprights 6, 7, an emphasis 22 is installed (Fig. 2). The emphasis 22 is made in the form of axes and is designed to prevent the loss of the upper sliders 17.

Racks 6 and 7 are interconnected through the cup of the chair 1, the pipe 23 and the braces 24 (figure 2).

Guide racks 6, 7 are equipped with an energy-absorbing device 3 (figure 4). The energy-absorbing device (Fig. 8) includes a body 26 (Fig. 7), with a curved plate 27 installed therein. The body of the energy-absorbing device is made in the form of a boxed part equipped with grooves 9, two eyes 25 at one end and a recess for mounting the plate. The grooves 9 are made on the walls of the housing. The niche is equipped with a stop 10, at which one end rests on the curved plate 27. The other end of the plate 27 is fixed with screws 20 on the lower slider 18. The housing 26 of the energy-absorbing device is rigidly mounted on the uprights 6 and 7 using the eyes 25 (Fig. 4).

The upper 17 and lower 18 sliders are mounted movably in the guide racks, while rigidly fixed to the chair cup 1 with uniaxial hinges 30 (Fig. 8).

Cup chair 1 (Fig.1-3) is made in the form of a monolithic product of a polymer composite material, for example, glass or carbon fiber and is equipped with soft elements. Chair cup 1 is installed on the pillars of the chair 6, 7 using the upper 17 and lower 18 sliders. In the upper part, the cup of the chair is equipped with a niche 8, designed for the passage of the shoulder straps 29 of the tethered system 4.

The soft elements of the chair cups are made of soft polyurethane foam and a refractory pad. Polyurethane foam seat cushion can be made of various degrees of softness, satisfying flight safety requirements. The chair cover for LA is made of genuine leather or fabric.

The tie system 4 is designed to fasten and hold a crew member or passenger in a chair during take-off and landing, as well as landing on land or water, in the event of overloads in an emergency. The attachment system 4 includes a shoulder belt 29, a left waist belt 16, a right waist belt 15 with a buckle 14, and an inertia coil 13 connected to the shoulder belt. The waist belts 16, 15 are attached to the cup of the chair 1 to the right and left using the attachment points 12. The inertial coil 13 of the harness 4 is installed behind the back of the cup of the chair 1.

The seat is equipped with a longitudinal adjustment mechanism, which includes a spring-loaded pin 11 (Figs. 5-6) connected to flexible cables 5, at the other end of which there is a control lever for longitudinal movement 28. The control lever for longitudinal movement 28 is mounted on the cup of the chair 1 from the bottom left. The longitudinal adjustment mechanism is equipped with cable tension regulators.

The operation of the energy-absorbing seat of an aircraft (for example, a helicopter) is as follows. Under operational loads, the chair cup 1, together with the person sitting on it, is kept from moving along the vertical struts 6, 7 using energy-absorbing devices 3 due to stiffness and friction. The deformation of the plate 27 serves to absorb energy. The main loads acting on the cup of the chair 1 in the longitudinal direction are perceived by the struts 6, 7. During emergency landing of LL, when the shock overload acting on the person sitting in the chair exceeds the permissible limits, the cup of the chair 1 moves down. In this case, the chair cup 1 acts through the lower sliders 18 on the plates 27 of the energy-absorbing devices 3. The plates 27, stretching out of the housing 26, absorb the energy of the shock load. In this case, the chair cup 1, with an inertial coil 13 mounted on its back with a tethered system 4, lower 18 and upper 17 sliders, moves down the guides relative to the vertical struts 6, 7.

If you need to move the chair along the rails 21, you must press the control lever for longitudinal movement 28. In this case, the spring-loaded pin 11 connected to the handle through the cable system 5 extends and allows the chair to move freely along the rails.

Thus, the use of this design allows you to optimize the loads coming on the chair during an emergency landing, significantly reduce the possibility of skewing of the sliders, which are subject to the maximum bending moment. Removing energy-absorbing devices into a separate mechanism allows you to reduce the weight of the struts of the chair, to simplify their design, which is important when using the chair on an aircraft. In addition, this design allows for quick access to all nodes of the energy-absorbing seat of the aircraft, thereby increasing its operational performance.

Claims (2)

1. Energy-absorbing seat of an aircraft, comprising a frame made in the form of racks, a cup of a chair and suspension units, characterized in that the racks are equipped with rails with an energy-absorbing device rigidly installed in each of them, which is made in the form of a boxed part provided with grooves for the racks of the racks , lugs for mounting on frame racks, a niche with an emphasis for installing a plate, the other end of which is fixed to the suspension unit, while the suspension units are made in the form of sliders movably mounted in n guiding racks. 2. The energy-absorbing seat of the aircraft according to claim 1, characterized in that the seat is equipped with a tethered system and a longitudinal adjustment mechanism mounted on the seat cup.

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